SD7003-085-88 (sd7003-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7003-085-88 (sd7003-il) Reynolds number: 100,000 Max Cl/Cd: 45.06 at α=6° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7003-il-100000-n5.txt Download as CSV file: xf-sd7003-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD7003-085-88
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
------ -------- --------- --------- -------- -------- --------
-9.250 -0.5632 0.08759 0.08257 -0.0102 1.0000 0.0259
-9.000 -0.5701 0.08168 0.07673 -0.0137 1.0000 0.0259
-8.750 -0.5801 0.07514 0.07027 -0.0181 1.0000 0.0257
-8.500 -0.6456 0.05301 0.04777 -0.0356 1.0000 0.0222
-8.000 -0.6367 0.04607 0.04048 -0.0375 1.0000 0.0237
-7.750 -0.6275 0.04268 0.03682 -0.0380 1.0000 0.0246
-7.500 -0.6185 0.03829 0.03194 -0.0383 1.0000 0.0254
-7.250 -0.6057 0.03415 0.02724 -0.0381 1.0000 0.0262
-7.000 -0.5892 0.03056 0.02304 -0.0375 1.0000 0.0275
-6.750 -0.5697 0.02765 0.01957 -0.0368 1.0000 0.0293
-6.500 -0.5483 0.02655 0.01846 -0.0364 1.0000 0.0321
-6.250 -0.5259 0.02497 0.01656 -0.0357 1.0000 0.0358
-6.000 -0.5035 0.02326 0.01463 -0.0349 1.0000 0.0393
-5.750 -0.4805 0.02236 0.01364 -0.0343 1.0000 0.0444
-5.500 -0.4573 0.02103 0.01208 -0.0334 1.0000 0.0495
-5.250 -0.4341 0.02019 0.01122 -0.0327 1.0000 0.0560
-5.000 -0.4108 0.01912 0.01003 -0.0319 1.0000 0.0620
-4.750 -0.3874 0.01839 0.00925 -0.0311 1.0000 0.0704
-4.500 -0.3642 0.01757 0.00842 -0.0304 1.0000 0.0783
-4.250 -0.3408 0.01689 0.00770 -0.0296 1.0000 0.0888
-4.000 -0.3172 0.01630 0.00709 -0.0288 1.0000 0.1009
-3.750 -0.2938 0.01571 0.00653 -0.0281 1.0000 0.1148
-3.500 -0.2705 0.01514 0.00604 -0.0274 1.0000 0.1330
-3.250 -0.2471 0.01463 0.00561 -0.0267 1.0000 0.1573
-3.000 -0.2241 0.01410 0.00527 -0.0261 1.0000 0.1934
-2.750 -0.2011 0.01362 0.00500 -0.0254 1.0000 0.2442
-2.500 -0.1785 0.01315 0.00479 -0.0247 1.0000 0.3079
-2.250 -0.1565 0.01270 0.00467 -0.0239 1.0000 0.3865
-2.000 -0.1220 0.01221 0.00462 -0.0255 0.9906 0.4989
-1.750 -0.0862 0.01180 0.00466 -0.0268 0.9775 0.6197
-1.500 -0.0520 0.01155 0.00469 -0.0274 0.9631 0.7208
-1.250 -0.0188 0.01137 0.00468 -0.0275 0.9475 0.7990
-1.000 0.0160 0.01123 0.00462 -0.0278 0.9309 0.8647
-0.750 0.0601 0.01110 0.00447 -0.0302 0.9145 0.9225
-0.500 0.1137 0.01097 0.00425 -0.0348 0.8962 0.9687
-0.250 0.1630 0.01087 0.00401 -0.0389 0.8721 1.0000
0.000 0.1949 0.01087 0.00386 -0.0394 0.8433 1.0000
0.250 0.2236 0.01091 0.00375 -0.0392 0.8134 1.0000
0.500 0.2503 0.01099 0.00366 -0.0386 0.7832 1.0000
0.750 0.2764 0.01110 0.00361 -0.0379 0.7531 1.0000
1.000 0.3022 0.01124 0.00359 -0.0371 0.7231 1.0000
1.250 0.3278 0.01140 0.00360 -0.0364 0.6931 1.0000
1.500 0.3533 0.01157 0.00363 -0.0356 0.6635 1.0000
1.750 0.3787 0.01177 0.00368 -0.0349 0.6340 1.0000
2.000 0.4041 0.01198 0.00375 -0.0341 0.6048 1.0000
2.250 0.4294 0.01221 0.00386 -0.0334 0.5760 1.0000
2.500 0.4548 0.01246 0.00397 -0.0328 0.5474 1.0000
2.750 0.4802 0.01272 0.00412 -0.0321 0.5192 1.0000
3.000 0.5056 0.01300 0.00430 -0.0315 0.4917 1.0000
3.250 0.5310 0.01330 0.00449 -0.0309 0.4644 1.0000
3.500 0.5563 0.01361 0.00470 -0.0304 0.4376 1.0000
3.750 0.5817 0.01394 0.00496 -0.0298 0.4108 1.0000
4.000 0.6070 0.01428 0.00523 -0.0293 0.3850 1.0000
4.250 0.6322 0.01465 0.00553 -0.0288 0.3599 1.0000
4.500 0.6573 0.01505 0.00585 -0.0283 0.3360 1.0000
4.750 0.6825 0.01545 0.00623 -0.0278 0.3119 1.0000
5.000 0.7073 0.01590 0.00662 -0.0273 0.2900 1.0000
5.250 0.7323 0.01635 0.00705 -0.0269 0.2682 1.0000
5.500 0.7569 0.01685 0.00750 -0.0264 0.2484 1.0000
5.750 0.7816 0.01735 0.00803 -0.0259 0.2288 1.0000
6.000 0.8061 0.01789 0.00857 -0.0254 0.2106 1.0000
6.250 0.8302 0.01847 0.00914 -0.0249 0.1935 1.0000
6.500 0.8540 0.01908 0.00976 -0.0244 0.1778 1.0000
6.750 0.8776 0.01973 0.01045 -0.0239 0.1629 1.0000
7.000 0.9010 0.02042 0.01116 -0.0233 0.1490 1.0000
7.250 0.9242 0.02113 0.01193 -0.0227 0.1357 1.0000
7.500 0.9471 0.02188 0.01276 -0.0221 0.1232 1.0000
7.750 0.9696 0.02269 0.01367 -0.0215 0.1114 1.0000
8.000 0.9915 0.02355 0.01461 -0.0209 0.0999 1.0000
8.250 1.0127 0.02447 0.01561 -0.0202 0.0891 1.0000
8.500 1.0330 0.02548 0.01667 -0.0194 0.0792 1.0000
8.750 1.0523 0.02655 0.01778 -0.0187 0.0699 1.0000
9.000 1.0722 0.02764 0.01909 -0.0179 0.0614 1.0000
9.250 1.0895 0.02900 0.02054 -0.0169 0.0549 1.0000
9.500 1.1063 0.03034 0.02202 -0.0159 0.0494 1.0000
9.750 1.1211 0.03195 0.02374 -0.0147 0.0450 1.0000
10.000 1.1357 0.03349 0.02548 -0.0136 0.0409 1.0000
10.250 1.1475 0.03522 0.02730 -0.0123 0.0384 1.0000
10.500 1.1576 0.03734 0.02958 -0.0109 0.0365 1.0000
10.750 1.1670 0.03951 0.03208 -0.0095 0.0347 1.0000
11.000 1.1736 0.04166 0.03446 -0.0081 0.0329 1.0000
11.250 1.1763 0.04369 0.03665 -0.0064 0.0315 1.0000
11.500 1.1763 0.04578 0.03885 -0.0048 0.0304 1.0000
11.750 1.1741 0.04829 0.04146 -0.0038 0.0295 1.0000
12.000 1.1681 0.05155 0.04489 -0.0033 0.0288 1.0000
12.250 1.1598 0.05532 0.04895 -0.0036 0.0284 1.0000
12.500 1.1486 0.05978 0.05368 -0.0050 0.0281 1.0000
12.750 1.1348 0.06503 0.05918 -0.0075 0.0279 1.0000
13.000 1.1184 0.07117 0.06556 -0.0110 0.0278 1.0000
13.250 1.0989 0.07845 0.07306 -0.0158 0.0278 1.0000
13.500 1.0773 0.08667 0.08148 -0.0214 0.0280 1.0000
13.750 1.0521 0.09632 0.09129 -0.0279 0.0282 1.0000
14.000 1.0235 0.10738 0.10249 -0.0353 0.0285 1.0000
14.250 0.9919 0.11999 0.11519 -0.0432 0.0289 1.0000
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Polar data table (+)
Polar graphs
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