NACA 63(2)A-015 (naca632a015-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: NACA 63(2)A-015 (naca632a015-il) Reynolds number: 100,000 Max Cl/Cd: 45.1 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-naca632a015-il-100000-n5.txt Download as CSV file: xf-naca632a015-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NACA 63(2)A-015
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.100 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.750 -0.5175 0.09050 0.08500 -0.0464 1.0000 0.0276
-11.500 -0.5286 0.08527 0.07976 -0.0491 1.0000 0.0274
-11.250 -0.5429 0.08026 0.07471 -0.0514 1.0000 0.0272
-11.000 -0.5606 0.07549 0.06987 -0.0533 1.0000 0.0270
-10.750 -0.5801 0.07116 0.06547 -0.0541 1.0000 0.0268
-10.500 -0.6009 0.06733 0.06153 -0.0538 1.0000 0.0267
-10.250 -0.6169 0.06436 0.05846 -0.0524 1.0000 0.0265
-10.000 -0.6367 0.06151 0.05549 -0.0495 1.0000 0.0264
-9.750 -0.6540 0.05924 0.05312 -0.0455 1.0000 0.0263
-9.500 -0.6696 0.05675 0.05048 -0.0413 1.0000 0.0263
-9.250 -0.6811 0.05420 0.04776 -0.0373 1.0000 0.0262
-9.000 -0.6893 0.05179 0.04516 -0.0333 1.0000 0.0262
-8.750 -0.6970 0.04930 0.04246 -0.0291 1.0000 0.0263
-8.500 -0.7028 0.04706 0.04002 -0.0248 1.0000 0.0263
-8.250 -0.7088 0.04497 0.03771 -0.0202 1.0000 0.0265
-8.000 -0.7038 0.04236 0.03477 -0.0176 0.9965 0.0267
-7.750 -0.6805 0.03867 0.03043 -0.0181 0.9863 0.0278
-7.500 -0.6506 0.03729 0.02904 -0.0199 0.9771 0.0290
-7.250 -0.6204 0.03518 0.02662 -0.0213 0.9685 0.0305
-7.000 -0.5893 0.03272 0.02378 -0.0222 0.9597 0.0316
-6.750 -0.5548 0.03034 0.02103 -0.0234 0.9525 0.0329
-6.500 -0.5199 0.02890 0.01955 -0.0253 0.9447 0.0345
-6.250 -0.4840 0.02752 0.01798 -0.0270 0.9371 0.0379
-6.000 -0.4486 0.02611 0.01656 -0.0287 0.9291 0.0404
-5.750 -0.4128 0.02483 0.01523 -0.0303 0.9213 0.0434
-5.500 -0.3801 0.02374 0.01414 -0.0314 0.9121 0.0476
-5.250 -0.3502 0.02284 0.01320 -0.0320 0.9021 0.0525
-5.000 -0.3221 0.02192 0.01232 -0.0324 0.8927 0.0577
-4.750 -0.2987 0.02133 0.01165 -0.0318 0.8807 0.0638
-4.500 -0.2769 0.02061 0.01094 -0.0310 0.8699 0.0700
-4.250 -0.2539 0.02002 0.01021 -0.0302 0.8596 0.0757
-4.000 -0.2345 0.01946 0.00960 -0.0288 0.8481 0.0826
-3.750 -0.2114 0.01892 0.00895 -0.0279 0.8388 0.0910
-3.500 -0.1907 0.01843 0.00840 -0.0266 0.8284 0.1041
-3.250 -0.1753 0.01743 0.00773 -0.0247 0.8187 0.1632
-3.000 -0.1793 0.01561 0.00751 -0.0192 0.8089 0.5172
-2.750 -0.1610 0.01552 0.00765 -0.0167 0.7995 0.5919
-2.500 -0.1382 0.01556 0.00769 -0.0151 0.7915 0.6356
-2.250 -0.1166 0.01566 0.00776 -0.0134 0.7823 0.6662
-2.000 -0.0924 0.01581 0.00792 -0.0119 0.7746 0.6968
-1.750 -0.0697 0.01606 0.00820 -0.0100 0.7661 0.7256
-1.500 -0.0437 0.01617 0.00826 -0.0090 0.7584 0.7433
-1.250 -0.0195 0.01614 0.00812 -0.0082 0.7503 0.7530
-1.000 0.0092 0.01614 0.00805 -0.0082 0.7424 0.7598
-0.750 0.0336 0.01610 0.00791 -0.0075 0.7349 0.7692
-0.500 0.0622 0.01613 0.00791 -0.0075 0.7267 0.7758
-0.250 0.0885 0.01611 0.00780 -0.0071 0.7197 0.7849
0.000 0.1155 0.01615 0.00783 -0.0069 0.7110 0.7923
0.250 0.1437 0.01614 0.00773 -0.0067 0.7045 0.8011
0.500 0.1697 0.01620 0.00780 -0.0064 0.6950 0.8090
0.750 0.1982 0.01618 0.00771 -0.0063 0.6874 0.8180
1.000 0.2248 0.01620 0.00773 -0.0059 0.6759 0.8261
1.250 0.2509 0.01618 0.00766 -0.0053 0.6638 0.8357
1.500 0.2804 0.01615 0.00758 -0.0054 0.6517 0.8436
1.750 0.3071 0.01613 0.00753 -0.0050 0.6396 0.8534
2.000 0.3367 0.01619 0.00760 -0.0052 0.6279 0.8615
2.250 0.3642 0.01622 0.00760 -0.0050 0.6178 0.8716
2.500 0.3967 0.01629 0.00768 -0.0058 0.6066 0.8791
2.750 0.4231 0.01636 0.00776 -0.0056 0.5949 0.8900
3.000 0.4578 0.01645 0.00785 -0.0069 0.5830 0.8967
3.250 0.4861 0.01650 0.00788 -0.0069 0.5714 0.9073
3.500 0.5210 0.01662 0.00802 -0.0084 0.5571 0.9140
3.750 0.5497 0.01672 0.00814 -0.0086 0.5430 0.9244
4.000 0.5855 0.01684 0.00827 -0.0103 0.5269 0.9309
4.250 0.6157 0.01697 0.00839 -0.0109 0.5106 0.9408
4.500 0.6525 0.01712 0.00854 -0.0129 0.4921 0.9470
4.750 0.6831 0.01729 0.00869 -0.0137 0.4727 0.9566
5.000 0.7181 0.01750 0.00889 -0.0155 0.4487 0.9640
5.250 0.7499 0.01774 0.00908 -0.0167 0.4249 0.9731
5.500 0.7821 0.01805 0.00933 -0.0181 0.3987 0.9825
5.750 0.8161 0.01840 0.00960 -0.0200 0.3726 0.9910
6.000 0.8502 0.01885 0.00995 -0.0220 0.3481 0.9998
6.250 0.8591 0.01920 0.01022 -0.0190 0.3329 1.0000
6.500 0.8677 0.01958 0.01054 -0.0159 0.3190 1.0000
6.750 0.8771 0.02000 0.01090 -0.0129 0.3061 1.0000
7.000 0.8872 0.02046 0.01128 -0.0101 0.2945 1.0000
7.250 0.8983 0.02092 0.01170 -0.0074 0.2839 1.0000
7.500 0.9107 0.02139 0.01217 -0.0050 0.2741 1.0000
7.750 0.9225 0.02192 0.01263 -0.0025 0.2657 1.0000
8.000 0.9359 0.02240 0.01316 -0.0003 0.2567 1.0000
8.250 0.9481 0.02295 0.01367 0.0021 0.2488 1.0000
8.500 0.9601 0.02346 0.01423 0.0045 0.2397 1.0000
8.750 0.9713 0.02404 0.01479 0.0069 0.2313 1.0000
9.000 0.9815 0.02460 0.01538 0.0095 0.2223 1.0000
9.250 0.9904 0.02518 0.01598 0.0122 0.2138 1.0000
9.500 0.9980 0.02578 0.01659 0.0151 0.2060 1.0000
9.750 1.0075 0.02641 0.01730 0.0176 0.1987 1.0000
10.000 1.0163 0.02709 0.01803 0.0200 0.1916 1.0000
10.250 1.0254 0.02784 0.01883 0.0222 0.1845 1.0000
10.500 1.0336 0.02863 0.01970 0.0243 0.1769 1.0000
10.750 1.0417 0.02951 0.02063 0.0263 0.1697 1.0000
11.000 1.0495 0.03044 0.02167 0.0282 0.1624 1.0000
11.250 1.0566 0.03148 0.02277 0.0299 0.1553 1.0000
11.500 1.0625 0.03262 0.02399 0.0316 0.1477 1.0000
11.750 1.0683 0.03387 0.02532 0.0331 0.1402 1.0000
12.000 1.0711 0.03532 0.02679 0.0345 0.1327 1.0000
12.250 1.0755 0.03682 0.02841 0.0357 0.1246 1.0000
12.500 1.0764 0.03859 0.03016 0.0368 0.1183 1.0000
12.750 1.0794 0.04039 0.03207 0.0376 0.1109 1.0000
13.000 1.0788 0.04250 0.03417 0.0384 0.1052 1.0000
13.250 1.0806 0.04456 0.03636 0.0390 0.0995 1.0000
13.500 1.0785 0.04699 0.03879 0.0393 0.0953 1.0000
13.750 1.0792 0.04933 0.04125 0.0397 0.0911 1.0000
14.000 1.0778 0.05193 0.04394 0.0398 0.0871 1.0000
14.250 1.0751 0.05469 0.04672 0.0397 0.0842 1.0000
14.500 1.0737 0.05749 0.04962 0.0396 0.0811 1.0000
14.750 1.0719 0.06043 0.05271 0.0393 0.0781 1.0000
15.000 1.0683 0.06365 0.05601 0.0387 0.0754 1.0000
15.250 1.0653 0.06681 0.05920 0.0381 0.0733 1.0000
15.500 1.0614 0.07034 0.06286 0.0372 0.0710 1.0000
15.750 1.0562 0.07418 0.06687 0.0361 0.0687 1.0000
16.000 1.0512 0.07802 0.07084 0.0349 0.0668 1.0000
16.250 1.0471 0.08181 0.07471 0.0336 0.0651 1.0000
16.500 1.0461 0.08509 0.07800 0.0326 0.0635 1.0000
16.750 1.0385 0.08970 0.08277 0.0309 0.0621 1.0000
17.000 1.0271 0.09511 0.08838 0.0285 0.0608 1.0000
17.250 1.0148 0.10082 0.09427 0.0259 0.0594 1.0000
17.500 1.0023 0.10672 0.10032 0.0231 0.0583 1.0000
17.750 0.9906 0.11260 0.10632 0.0201 0.0572 1.0000
18.000 0.9872 0.11685 0.11061 0.0181 0.0558 1.0000
18.250 0.9919 0.11945 0.11318 0.0172 0.0545 1.0000
18.500 0.9571 0.13066 0.12465 0.0109 0.0541 1.0000
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