MH 95 15.86% (mh95-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: MH 95 15.86% (mh95-il) Reynolds number: 500,000 Max Cl/Cd: 60.83 at α=7.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-mh95-il-500000-n5.txt Download as CSV file: xf-mh95-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: MH 95 15.86%
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-17.750 -0.7652 0.10892 0.10545 -0.0540 1.0000 0.0114
-17.500 -0.7982 0.09860 0.09493 -0.0596 1.0000 0.0114
-17.250 -0.8233 0.09033 0.08648 -0.0639 1.0000 0.0113
-17.000 -0.8453 0.08300 0.07898 -0.0677 1.0000 0.0113
-16.750 -0.8622 0.07686 0.07270 -0.0706 1.0000 0.0114
-16.500 -0.8786 0.07115 0.06683 -0.0731 1.0000 0.0114
-16.250 -0.8911 0.06630 0.06185 -0.0749 1.0000 0.0114
-16.000 -0.9010 0.06211 0.05753 -0.0762 1.0000 0.0114
-15.750 -0.9104 0.05825 0.05354 -0.0771 1.0000 0.0115
-15.500 -0.9177 0.05490 0.05008 -0.0775 1.0000 0.0115
-15.250 -0.9250 0.05178 0.04684 -0.0774 1.0000 0.0115
-15.000 -0.9312 0.04901 0.04396 -0.0769 1.0000 0.0116
-14.750 -0.9364 0.04654 0.04138 -0.0761 1.0000 0.0116
-14.500 -0.9418 0.04421 0.03894 -0.0749 1.0000 0.0118
-14.250 -0.9456 0.04219 0.03682 -0.0734 1.0000 0.0118
-14.000 -0.9493 0.04029 0.03482 -0.0716 1.0000 0.0118
-13.750 -0.9523 0.03859 0.03303 -0.0695 1.0000 0.0120
-13.500 -0.9545 0.03707 0.03142 -0.0673 1.0000 0.0120
-13.250 -0.9552 0.03554 0.02981 -0.0651 0.9999 0.0121
-13.000 -0.9412 0.03394 0.02810 -0.0657 0.9987 0.0122
-12.750 -0.9269 0.03238 0.02643 -0.0660 0.9971 0.0123
-12.500 -0.9113 0.03105 0.02501 -0.0663 0.9955 0.0124
-12.250 -0.8934 0.02988 0.02372 -0.0668 0.9939 0.0126
-12.000 -0.8759 0.02878 0.02253 -0.0669 0.9922 0.0127
-11.750 -0.8638 0.02731 0.02103 -0.0663 0.9898 0.0129
-11.500 -0.8467 0.02621 0.01988 -0.0663 0.9875 0.0131
-11.250 -0.8275 0.02520 0.01881 -0.0665 0.9855 0.0132
-11.000 -0.8066 0.02424 0.01782 -0.0669 0.9838 0.0134
-10.750 -0.7838 0.02335 0.01689 -0.0675 0.9825 0.0136
-10.500 -0.7671 0.02254 0.01603 -0.0667 0.9794 0.0138
-10.250 -0.7490 0.02179 0.01524 -0.0661 0.9760 0.0140
-10.000 -0.7276 0.02101 0.01442 -0.0661 0.9735 0.0142
-9.750 -0.7032 0.02028 0.01364 -0.0665 0.9716 0.0145
-9.500 -0.6770 0.01959 0.01290 -0.0673 0.9701 0.0148
-9.250 -0.6582 0.01896 0.01224 -0.0664 0.9666 0.0150
-9.000 -0.6404 0.01840 0.01163 -0.0652 0.9620 0.0153
-8.750 -0.6157 0.01782 0.01100 -0.0653 0.9594 0.0155
-8.500 -0.5899 0.01712 0.01029 -0.0657 0.9575 0.0159
-8.250 -0.5613 0.01650 0.00965 -0.0666 0.9560 0.0164
-8.000 -0.5453 0.01610 0.00923 -0.0646 0.9508 0.0167
-7.750 -0.5248 0.01566 0.00878 -0.0636 0.9464 0.0172
-7.500 -0.4980 0.01520 0.00829 -0.0637 0.9437 0.0179
-7.250 -0.4685 0.01477 0.00783 -0.0644 0.9417 0.0185
-7.000 -0.4390 0.01427 0.00733 -0.0652 0.9398 0.0196
-6.750 -0.4280 0.01402 0.00707 -0.0619 0.9319 0.0204
-6.500 -0.4016 0.01366 0.00669 -0.0618 0.9282 0.0216
-6.250 -0.3730 0.01324 0.00627 -0.0622 0.9253 0.0232
-6.000 -0.3520 0.01295 0.00598 -0.0609 0.9199 0.0254
-5.750 -0.3309 0.01263 0.00567 -0.0597 0.9137 0.0289
-5.500 -0.3034 0.01225 0.00532 -0.0598 0.9096 0.0360
-5.250 -0.2816 0.01188 0.00502 -0.0587 0.9036 0.0498
-5.000 -0.2614 0.01148 0.00473 -0.0574 0.8963 0.0707
-4.750 -0.2350 0.01097 0.00436 -0.0574 0.8914 0.1048
-4.500 -0.2186 0.01054 0.00411 -0.0552 0.8822 0.1454
-4.250 -0.1941 0.01005 0.00381 -0.0548 0.8754 0.1923
-4.000 -0.1737 0.00970 0.00359 -0.0535 0.8661 0.2305
-3.750 -0.1494 0.00924 0.00332 -0.0530 0.8577 0.2835
-3.500 -0.1316 0.00874 0.00309 -0.0512 0.8466 0.3520
-3.250 -0.1116 0.00822 0.00285 -0.0499 0.8359 0.4285
-3.000 -0.0923 0.00770 0.00263 -0.0483 0.8239 0.5107
-2.750 -0.0715 0.00737 0.00253 -0.0469 0.8107 0.5756
-2.500 -0.0462 0.00726 0.00245 -0.0462 0.7971 0.6084
-2.250 -0.0202 0.00721 0.00239 -0.0457 0.7822 0.6295
-2.000 0.0058 0.00720 0.00234 -0.0451 0.7655 0.6464
-1.750 0.0314 0.00723 0.00230 -0.0445 0.7479 0.6607
-1.500 0.0566 0.00726 0.00228 -0.0438 0.7297 0.6729
-1.250 0.0816 0.00732 0.00226 -0.0430 0.7109 0.6832
-1.000 0.1062 0.00739 0.00226 -0.0422 0.6917 0.6937
-0.750 0.1308 0.00747 0.00226 -0.0414 0.6738 0.7026
-0.500 0.1552 0.00756 0.00228 -0.0405 0.6549 0.7119
-0.250 0.1795 0.00765 0.00230 -0.0397 0.6368 0.7198
0.000 0.2035 0.00775 0.00233 -0.0388 0.6176 0.7271
0.250 0.2276 0.00787 0.00235 -0.0380 0.5985 0.7339
0.500 0.2511 0.00798 0.00240 -0.0369 0.5782 0.7394
0.750 0.2746 0.00811 0.00245 -0.0360 0.5583 0.7455
1.250 0.3209 0.00840 0.00258 -0.0339 0.5169 0.7573
1.500 0.3440 0.00856 0.00266 -0.0329 0.4958 0.7635
1.750 0.3670 0.00873 0.00272 -0.0319 0.4734 0.7692
2.000 0.3893 0.00890 0.00282 -0.0308 0.4512 0.7738
2.250 0.4109 0.00911 0.00293 -0.0295 0.4258 0.7787
2.500 0.4320 0.00936 0.00304 -0.0282 0.3964 0.7838
3.000 0.4755 0.00982 0.00328 -0.0259 0.3467 0.7920
3.250 0.4980 0.01001 0.00341 -0.0249 0.3294 0.7959
3.500 0.5202 0.01021 0.00353 -0.0238 0.3124 0.8000
3.750 0.5423 0.01040 0.00365 -0.0227 0.2964 0.8042
4.000 0.5642 0.01060 0.00378 -0.0216 0.2818 0.8078
4.250 0.5857 0.01079 0.00393 -0.0204 0.2689 0.8113
4.500 0.6072 0.01098 0.00409 -0.0193 0.2564 0.8153
4.750 0.6292 0.01118 0.00425 -0.0182 0.2445 0.8193
5.000 0.6509 0.01141 0.00442 -0.0171 0.2322 0.8233
5.250 0.6722 0.01165 0.00462 -0.0160 0.2206 0.8270
5.500 0.6936 0.01186 0.00482 -0.0148 0.2103 0.8309
5.750 0.7148 0.01210 0.00503 -0.0137 0.2008 0.8350
6.000 0.7357 0.01237 0.00525 -0.0125 0.1901 0.8391
6.250 0.7571 0.01262 0.00548 -0.0115 0.1793 0.8434
6.500 0.7771 0.01289 0.00573 -0.0101 0.1696 0.8473
6.750 0.7965 0.01319 0.00599 -0.0087 0.1595 0.8518
7.000 0.8170 0.01345 0.00625 -0.0075 0.1509 0.8564
7.250 0.8367 0.01378 0.00654 -0.0063 0.1425 0.8610
7.500 0.8559 0.01407 0.00683 -0.0048 0.1348 0.8653
7.750 0.8743 0.01439 0.00714 -0.0033 0.1281 0.8705
8.000 0.8931 0.01472 0.00747 -0.0019 0.1215 0.8760
8.250 0.9115 0.01507 0.00781 -0.0005 0.1165 0.8810
8.500 0.9296 0.01537 0.00814 0.0010 0.1119 0.8862
8.750 0.9469 0.01574 0.00852 0.0026 0.1079 0.8925
9.000 0.9640 0.01611 0.00890 0.0042 0.1045 0.8988
9.250 0.9813 0.01642 0.00927 0.0058 0.1019 0.9059
9.750 1.0132 0.01720 0.01011 0.0093 0.0964 0.9217
10.000 1.0280 0.01764 0.01058 0.0111 0.0937 0.9317
10.500 1.0678 0.01845 0.01153 0.0127 0.0900 0.9581
10.750 1.0957 0.01900 0.01212 0.0115 0.0878 0.9741
11.000 1.1160 0.01957 0.01270 0.0118 0.0859 1.0000
11.250 1.1311 0.02020 0.01334 0.0131 0.0843 1.0000
11.500 1.1461 0.02084 0.01401 0.0144 0.0829 1.0000
11.750 1.1625 0.02141 0.01463 0.0154 0.0818 1.0000
12.000 1.1778 0.02204 0.01531 0.0166 0.0804 1.0000
12.250 1.1923 0.02273 0.01604 0.0178 0.0792 1.0000
12.500 1.2060 0.02348 0.01682 0.0190 0.0779 1.0000
12.750 1.2188 0.02429 0.01767 0.0202 0.0769 1.0000
13.000 1.2301 0.02521 0.01862 0.0215 0.0755 1.0000
13.250 1.2399 0.02626 0.01970 0.0229 0.0744 1.0000
13.500 1.2509 0.02725 0.02075 0.0241 0.0735 1.0000
13.750 1.2635 0.02817 0.02173 0.0250 0.0726 1.0000
14.000 1.2749 0.02919 0.02283 0.0260 0.0718 1.0000
14.250 1.2857 0.03028 0.02399 0.0269 0.0708 1.0000
14.500 1.2958 0.03146 0.02523 0.0278 0.0699 1.0000
14.750 1.3049 0.03275 0.02656 0.0286 0.0688 1.0000
15.000 1.3131 0.03415 0.02801 0.0294 0.0678 1.0000
15.250 1.3197 0.03573 0.02964 0.0301 0.0668 1.0000
15.500 1.3245 0.03752 0.03148 0.0308 0.0659 1.0000
15.750 1.3295 0.03934 0.03337 0.0313 0.0651 1.0000
16.000 1.3382 0.04090 0.03503 0.0316 0.0642 1.0000
16.250 1.3446 0.04272 0.03693 0.0318 0.0636 1.0000
16.500 1.3509 0.04460 0.03889 0.0319 0.0627 1.0000
16.750 1.3560 0.04665 0.04103 0.0319 0.0618 1.0000
17.000 1.3599 0.04888 0.04334 0.0318 0.0609 1.0000
17.250 1.3626 0.05130 0.04583 0.0316 0.0601 1.0000
17.500 1.3642 0.05393 0.04852 0.0312 0.0594 1.0000
17.750 1.3637 0.05685 0.05152 0.0306 0.0586 1.0000
18.000 1.3612 0.06007 0.05480 0.0298 0.0580 1.0000
18.250 1.3612 0.06309 0.05792 0.0290 0.0573 1.0000
18.500 1.3620 0.06608 0.06102 0.0281 0.0567 1.0000
18.750 1.3622 0.06923 0.06428 0.0270 0.0560 1.0000
19.000 1.3608 0.07263 0.06779 0.0258 0.0551 1.0000
19.250 1.3580 0.07627 0.07153 0.0244 0.0545 1.0000
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