SD7003-085-88 (sd7003-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: SD7003-085-88 (sd7003-il) Reynolds number: 100,000 Max Cl/Cd: 43.33 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-sd7003-il-100000.txt Download as CSV file: xf-sd7003-il-100000.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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.000 -0.5197 0.10154 0.09654 -0.0015 1.0000 0.1091
-8.750 -0.5400 0.09832 0.09345 -0.0081 1.0000 0.1140
-8.500 -0.5614 0.09446 0.08974 -0.0151 1.0000 0.1146
-8.250 -0.5197 0.09015 0.08532 -0.0066 1.0000 0.1200
-8.000 -0.5203 0.08668 0.08191 -0.0082 1.0000 0.1246
-7.750 -0.5630 0.08141 0.07669 -0.0244 1.0000 0.1289
-7.500 -0.5350 0.07783 0.07322 -0.0159 1.0000 0.1319
-7.250 -0.5256 0.07454 0.06994 -0.0157 1.0000 0.1366
-7.000 -0.5374 0.06830 0.06363 -0.0250 1.0000 0.1449
-6.750 -0.5468 0.04834 0.04275 -0.0368 1.0000 0.0757
-6.500 -0.5340 0.04258 0.03661 -0.0372 1.0000 0.0687
-6.250 -0.5205 0.03708 0.03054 -0.0374 1.0000 0.0665
-6.000 -0.5023 0.03347 0.02639 -0.0369 1.0000 0.0693
-5.750 -0.4820 0.02998 0.02221 -0.0362 1.0000 0.0716
-5.500 -0.4605 0.02681 0.01852 -0.0354 1.0000 0.0751
-5.250 -0.4378 0.02525 0.01689 -0.0347 1.0000 0.0827
-5.000 -0.4141 0.02305 0.01431 -0.0338 1.0000 0.0895
-4.750 -0.3900 0.02176 0.01282 -0.0329 1.0000 0.0994
-4.500 -0.3664 0.02028 0.01131 -0.0321 1.0000 0.1105
-4.250 -0.3424 0.01896 0.00997 -0.0312 1.0000 0.1229
-4.000 -0.3185 0.01793 0.00893 -0.0304 1.0000 0.1390
-3.750 -0.2946 0.01700 0.00796 -0.0295 1.0000 0.1576
-3.500 -0.2716 0.01599 0.00717 -0.0286 1.0000 0.1798
-3.250 -0.2486 0.01512 0.00649 -0.0277 1.0000 0.2134
-3.000 -0.2263 0.01412 0.00589 -0.0268 1.0000 0.2693
-2.750 -0.2053 0.01298 0.00547 -0.0258 1.0000 0.3866
-2.500 -0.1869 0.01207 0.00534 -0.0238 1.0000 0.5476
-2.250 -0.1718 0.01163 0.00543 -0.0204 1.0000 0.6850
-2.000 -0.1590 0.01144 0.00552 -0.0163 1.0000 0.7865
-1.750 -0.1456 0.01133 0.00557 -0.0121 1.0000 0.8773
-1.500 -0.0785 0.01120 0.00531 -0.0187 1.0000 1.0000
-1.250 -0.0657 0.01122 0.00517 -0.0173 1.0000 1.0000
-1.000 -0.0485 0.01134 0.00514 -0.0165 1.0000 1.0000
-0.750 -0.0307 0.01155 0.00521 -0.0159 1.0000 1.0000
-0.500 -0.0037 0.01186 0.00539 -0.0170 0.9966 1.0000
-0.250 0.0572 0.01217 0.00558 -0.0241 0.9801 1.0000
0.000 0.1155 0.01231 0.00564 -0.0303 0.9620 1.0000
0.250 0.1754 0.01229 0.00557 -0.0364 0.9447 1.0000
0.500 0.2321 0.01215 0.00541 -0.0416 0.9263 1.0000
0.750 0.2775 0.01200 0.00524 -0.0443 0.9017 1.0000
1.000 0.3164 0.01189 0.00508 -0.0456 0.8741 1.0000
1.250 0.3480 0.01185 0.00497 -0.0453 0.8439 1.0000
1.500 0.3750 0.01190 0.00492 -0.0441 0.8122 1.0000
1.750 0.3999 0.01201 0.00491 -0.0426 0.7803 1.0000
2.000 0.4240 0.01218 0.00495 -0.0410 0.7481 1.0000
2.250 0.4478 0.01239 0.00503 -0.0396 0.7147 1.0000
2.500 0.4718 0.01263 0.00513 -0.0382 0.6818 1.0000
2.750 0.4959 0.01289 0.00524 -0.0369 0.6494 1.0000
3.000 0.5202 0.01318 0.00540 -0.0357 0.6173 1.0000
3.250 0.5446 0.01350 0.00557 -0.0346 0.5853 1.0000
3.500 0.5690 0.01384 0.00579 -0.0336 0.5524 1.0000
3.750 0.5935 0.01420 0.00603 -0.0326 0.5201 1.0000
4.000 0.6180 0.01460 0.00633 -0.0317 0.4887 1.0000
4.250 0.6425 0.01503 0.00663 -0.0308 0.4578 1.0000
4.500 0.6669 0.01550 0.00698 -0.0300 0.4277 1.0000
4.750 0.6914 0.01599 0.00737 -0.0292 0.3984 1.0000
5.000 0.7158 0.01652 0.00783 -0.0285 0.3701 1.0000
5.250 0.7401 0.01710 0.00832 -0.0278 0.3430 1.0000
5.500 0.7644 0.01772 0.00885 -0.0271 0.3177 1.0000
5.750 0.7886 0.01838 0.00943 -0.0264 0.2935 1.0000
6.000 0.8127 0.01907 0.01013 -0.0258 0.2700 1.0000
6.250 0.8367 0.01984 0.01077 -0.0251 0.2493 1.0000
6.500 0.8605 0.02063 0.01163 -0.0244 0.2284 1.0000
6.750 0.8842 0.02147 0.01247 -0.0238 0.2096 1.0000
7.000 0.9078 0.02241 0.01333 -0.0232 0.1925 1.0000
7.250 0.9311 0.02344 0.01437 -0.0225 0.1761 1.0000
7.500 0.9539 0.02450 0.01553 -0.0218 0.1603 1.0000
7.750 0.9761 0.02560 0.01672 -0.0210 0.1451 1.0000
8.000 0.9978 0.02676 0.01798 -0.0202 0.1306 1.0000
8.250 1.0187 0.02802 0.01933 -0.0193 0.1170 1.0000
8.500 1.0391 0.02943 0.02080 -0.0185 0.1044 1.0000
8.750 1.0589 0.03101 0.02241 -0.0176 0.0934 1.0000
9.000 1.0786 0.03268 0.02421 -0.0166 0.0842 1.0000
9.250 1.0953 0.03505 0.02699 -0.0154 0.0766 1.0000
9.500 1.1144 0.03736 0.02918 -0.0148 0.0704 1.0000
9.750 1.1253 0.04051 0.03299 -0.0131 0.0672 1.0000
10.000 1.1349 0.04371 0.03665 -0.0116 0.0641 1.0000
10.250 1.1479 0.04599 0.03908 -0.0106 0.0607 1.0000
10.500 1.1546 0.05001 0.04321 -0.0098 0.0581 1.0000
10.750 1.1483 0.05390 0.04766 -0.0079 0.0574 1.0000
11.000 1.1363 0.05826 0.05245 -0.0063 0.0571 1.0000
11.250 1.1180 0.06251 0.05701 -0.0048 0.0571 1.0000
11.500 1.0958 0.06684 0.06156 -0.0040 0.0572 1.0000
11.750 1.0727 0.07197 0.06687 -0.0053 0.0575 1.0000
12.000 1.0484 0.07822 0.07326 -0.0085 0.0579 1.0000
12.250 1.0257 0.08552 0.08067 -0.0128 0.0584 1.0000
12.500 0.8646 0.13346 0.12860 -0.0485 0.0843 1.0000
12.750 0.8815 0.13549 0.13070 -0.0461 0.0827 1.0000
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Polar data table (+)
Polar graphs
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