MB253515 15.0% smoothed (mb253515sm-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: MB253515 15.0% smoothed (mb253515sm-il) Reynolds number: 1,000,000 Max Cl/Cd: 105.78 at α=5.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-mb253515sm-il-1000000.txt Download as CSV file: xf-mb253515sm-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: MB253515 15.0% smoothed
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.750 -0.8631 0.06565 0.06331 -0.0636 1.0000 0.0090
-15.500 -0.8847 0.05850 0.05599 -0.0681 1.0000 0.0089
-15.250 -0.9052 0.05215 0.04946 -0.0718 1.0000 0.0089
-15.000 -0.9168 0.04756 0.04472 -0.0740 1.0000 0.0089
-14.750 -0.9421 0.04184 0.03878 -0.0759 1.0000 0.0090
-14.500 -0.9528 0.03826 0.03505 -0.0764 1.0000 0.0091
-14.250 -0.9540 0.03596 0.03265 -0.0763 1.0000 0.0093
-14.000 -0.9541 0.03393 0.03053 -0.0757 1.0000 0.0094
-13.750 -0.9506 0.03239 0.02892 -0.0748 1.0000 0.0095
-13.500 -0.9511 0.03060 0.02703 -0.0734 1.0000 0.0096
-13.250 -0.9454 0.02949 0.02585 -0.0719 1.0000 0.0098
-13.000 -0.9379 0.02867 0.02499 -0.0703 1.0000 0.0100
-12.750 -0.9317 0.02783 0.02410 -0.0682 1.0000 0.0102
-12.500 -0.9339 0.02641 0.02255 -0.0650 1.0000 0.0103
-12.250 -0.9310 0.02567 0.02173 -0.0618 1.0000 0.0106
-12.000 -0.9340 0.02482 0.02078 -0.0574 1.0000 0.0107
-11.750 -0.9118 0.02378 0.01962 -0.0578 0.9973 0.0111
-11.500 -0.8877 0.02272 0.01843 -0.0585 0.9875 0.0113
-11.250 -0.8651 0.02116 0.01668 -0.0591 0.9770 0.0117
-11.000 -0.8327 0.02006 0.01552 -0.0614 0.9691 0.0123
-10.750 -0.7912 0.01977 0.01523 -0.0650 0.9605 0.0128
-10.500 -0.7475 0.01944 0.01485 -0.0691 0.9502 0.0133
-10.250 -0.7070 0.01876 0.01403 -0.0726 0.9341 0.0141
-10.000 -0.6776 0.01813 0.01323 -0.0737 0.9121 0.0145
-9.750 -0.6570 0.01781 0.01276 -0.0726 0.8915 0.0148
-9.500 -0.6436 0.01672 0.01152 -0.0706 0.8741 0.0156
-9.250 -0.6253 0.01639 0.01112 -0.0690 0.8595 0.0160
-9.000 -0.6050 0.01631 0.01096 -0.0678 0.8466 0.0165
-8.750 -0.5853 0.01599 0.01055 -0.0665 0.8350 0.0170
-8.500 -0.5639 0.01583 0.01033 -0.0655 0.8246 0.0177
-8.250 -0.5423 0.01567 0.01006 -0.0644 0.8149 0.0184
-8.000 -0.5206 0.01540 0.00970 -0.0634 0.8055 0.0188
-7.750 -0.5033 0.01434 0.00856 -0.0618 0.7968 0.0197
-7.500 -0.4823 0.01401 0.00817 -0.0608 0.7887 0.0204
-7.250 -0.4594 0.01377 0.00791 -0.0600 0.7809 0.0211
-7.000 -0.4368 0.01353 0.00760 -0.0591 0.7732 0.0219
-6.750 -0.4134 0.01327 0.00731 -0.0584 0.7660 0.0228
-6.500 -0.3901 0.01303 0.00700 -0.0577 0.7591 0.0235
-6.250 -0.3649 0.01295 0.00687 -0.0572 0.7526 0.0240
-6.000 -0.3494 0.01196 0.00579 -0.0552 0.7457 0.0252
-5.750 -0.3279 0.01157 0.00536 -0.0541 0.7396 0.0262
-5.500 -0.3043 0.01132 0.00509 -0.0534 0.7334 0.0273
-5.250 -0.2813 0.01106 0.00477 -0.0526 0.7274 0.0281
-5.000 -0.2574 0.01078 0.00447 -0.0519 0.7216 0.0290
-4.750 -0.2332 0.01057 0.00421 -0.0513 0.7157 0.0298
-4.500 -0.2085 0.01042 0.00400 -0.0507 0.7104 0.0305
-4.250 -0.1855 0.01006 0.00359 -0.0499 0.7047 0.0314
-4.000 -0.1625 0.00975 0.00321 -0.0490 0.6992 0.0329
-3.750 -0.1378 0.00954 0.00296 -0.0484 0.6941 0.0343
-3.500 -0.1125 0.00937 0.00277 -0.0480 0.6883 0.0358
-3.000 -0.0616 0.00911 0.00242 -0.0471 0.6744 0.0387
-2.750 -0.0367 0.00898 0.00224 -0.0465 0.6671 0.0421
-2.500 -0.0113 0.00880 0.00209 -0.0461 0.6611 0.0522
-2.250 -0.0001 0.00763 0.00173 -0.0433 0.6556 0.2760
-2.000 0.0175 0.00703 0.00157 -0.0416 0.6506 0.4053
-1.750 0.0384 0.00662 0.00148 -0.0404 0.6453 0.4967
-1.500 0.0603 0.00636 0.00142 -0.0393 0.6401 0.5670
-1.250 0.0832 0.00620 0.00140 -0.0383 0.6353 0.6191
-1.000 0.1077 0.00607 0.00139 -0.0377 0.6302 0.6590
-0.750 0.1329 0.00602 0.00138 -0.0371 0.6248 0.6835
-0.500 0.1585 0.00599 0.00138 -0.0367 0.6196 0.7070
-0.250 0.1841 0.00594 0.00138 -0.0362 0.6141 0.7290
0.000 0.2097 0.00593 0.00139 -0.0357 0.6087 0.7486
0.250 0.2358 0.00592 0.00141 -0.0354 0.6035 0.7637
0.500 0.2620 0.00591 0.00142 -0.0351 0.5974 0.7798
0.750 0.2875 0.00592 0.00144 -0.0346 0.5917 0.7950
1.000 0.3144 0.00592 0.00147 -0.0344 0.5862 0.8060
1.250 0.3407 0.00594 0.00149 -0.0342 0.5799 0.8170
1.500 0.3669 0.00596 0.00152 -0.0339 0.5737 0.8282
1.750 0.3933 0.00597 0.00155 -0.0336 0.5669 0.8389
2.000 0.4191 0.00601 0.00159 -0.0333 0.5605 0.8503
2.250 0.4455 0.00603 0.00163 -0.0330 0.5535 0.8616
2.500 0.4712 0.00608 0.00169 -0.0326 0.5459 0.8730
2.750 0.4977 0.00610 0.00175 -0.0324 0.5377 0.8847
3.000 0.5235 0.00616 0.00181 -0.0320 0.5299 0.8973
3.250 0.5499 0.00621 0.00189 -0.0318 0.5208 0.9099
3.500 0.5772 0.00628 0.00197 -0.0318 0.5110 0.9215
3.750 0.6060 0.00639 0.00207 -0.0321 0.5001 0.9317
4.000 0.6352 0.00651 0.00219 -0.0326 0.4886 0.9418
4.250 0.6677 0.00665 0.00232 -0.0338 0.4754 0.9499
4.500 0.6995 0.00683 0.00246 -0.0349 0.4602 0.9573
4.750 0.7341 0.00704 0.00263 -0.0367 0.4445 0.9621
5.000 0.7628 0.00727 0.00280 -0.0371 0.4281 0.9696
5.250 0.7986 0.00755 0.00300 -0.0392 0.4054 0.9718
5.500 0.8312 0.00792 0.00325 -0.0407 0.3784 0.9749
5.750 0.8621 0.00824 0.00349 -0.0418 0.3587 0.9790
6.000 0.8914 0.00856 0.00374 -0.0426 0.3409 0.9835
6.500 0.9587 0.00917 0.00422 -0.0460 0.3077 0.9882
6.750 0.9904 0.00949 0.00448 -0.0474 0.2885 0.9915
7.000 1.0203 0.00994 0.00481 -0.0485 0.2603 0.9946
7.250 1.0473 0.01093 0.00541 -0.0495 0.1944 0.9982
7.500 1.0309 0.01274 0.00658 -0.0424 0.0828 1.0000
7.750 1.0149 0.01357 0.00721 -0.0342 0.0429 1.0000
8.000 1.0105 0.01408 0.00765 -0.0283 0.0288 1.0000
8.250 1.0150 0.01457 0.00811 -0.0242 0.0224 1.0000
8.500 1.0253 0.01498 0.00854 -0.0214 0.0201 1.0000
8.750 1.0342 0.01554 0.00910 -0.0185 0.0176 1.0000
9.000 1.0444 0.01612 0.00973 -0.0159 0.0163 1.0000
9.250 1.0573 0.01664 0.01028 -0.0139 0.0153 1.0000
9.500 1.0692 0.01726 0.01093 -0.0119 0.0145 1.0000
9.750 1.0779 0.01810 0.01180 -0.0097 0.0134 1.0000
10.000 1.0855 0.01907 0.01284 -0.0074 0.0127 1.0000
10.250 1.0970 0.01990 0.01372 -0.0058 0.0125 1.0000
10.500 1.1066 0.02088 0.01477 -0.0041 0.0121 1.0000
10.750 1.1188 0.02175 0.01568 -0.0029 0.0116 1.0000
11.000 1.1268 0.02296 0.01694 -0.0013 0.0113 1.0000
11.250 1.1361 0.02412 0.01814 -0.0001 0.0108 1.0000
11.500 1.1427 0.02553 0.01959 0.0013 0.0102 1.0000
11.750 1.1415 0.02759 0.02175 0.0030 0.0099 1.0000
12.000 1.1416 0.02966 0.02391 0.0044 0.0096 1.0000
12.250 1.1486 0.03123 0.02554 0.0053 0.0095 1.0000
12.500 1.1570 0.03270 0.02707 0.0060 0.0093 1.0000
12.750 1.1612 0.03460 0.02905 0.0069 0.0091 1.0000
13.000 1.1637 0.03669 0.03120 0.0076 0.0090 1.0000
13.250 1.1676 0.03871 0.03330 0.0083 0.0087 1.0000
13.500 1.1711 0.04085 0.03549 0.0088 0.0085 1.0000
13.750 1.1732 0.04316 0.03788 0.0092 0.0084 1.0000
14.000 1.1771 0.04536 0.04014 0.0095 0.0081 1.0000
14.250 1.1758 0.04812 0.04299 0.0098 0.0082 1.0000
14.500 1.1808 0.05034 0.04524 0.0098 0.0078 1.0000
14.750 1.1791 0.05326 0.04823 0.0099 0.0078 1.0000
15.000 1.1805 0.05592 0.05095 0.0099 0.0076 1.0000
15.250 1.1772 0.05909 0.05420 0.0099 0.0075 1.0000
15.500 1.1701 0.06261 0.05778 0.0101 0.0073 1.0000
15.750 1.1637 0.06576 0.06102 0.0110 0.0072 1.0000
16.000 1.1667 0.06840 0.06374 0.0107 0.0072 1.0000
16.250 1.1694 0.07112 0.06653 0.0104 0.0071 1.0000
16.500 1.1734 0.07401 0.06951 0.0094 0.0070 1.0000
16.750 1.1755 0.07698 0.07257 0.0087 0.0068 1.0000
17.000 1.1765 0.08012 0.07579 0.0079 0.0066 1.0000
17.250 1.1751 0.08311 0.07887 0.0080 0.0067 1.0000
17.500 1.1754 0.08641 0.08226 0.0071 0.0066 1.0000
17.750 1.1759 0.08979 0.08571 0.0060 0.0064 1.0000
18.000 1.1747 0.09326 0.08927 0.0050 0.0063 1.0000
18.250 1.1725 0.09676 0.09286 0.0043 0.0063 1.0000
18.500 1.1702 0.10047 0.09667 0.0032 0.0062 1.0000
18.750 1.1685 0.10445 0.10071 0.0015 0.0059 1.0000
19.000 1.1645 0.10833 0.10470 0.0004 0.0059 1.0000
19.250 1.1618 0.11221 0.10867 -0.0010 0.0059 1.0000
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Polar data table (+)
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