SD7037-092-88 (sd7037-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: SD7037-092-88 (sd7037-il) Reynolds number: 100,000 Max Cl/Cd: 55.44 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-sd7037-il-100000-n5.txt Download as CSV file: xf-sd7037-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: SD7037-092-88
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
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3778 0.08804 0.08314 -0.0346 1.0000 0.0384
-8.000 -0.3935 0.08256 0.07776 -0.0371 1.0000 0.0316
-7.750 -0.3982 0.08013 0.07541 -0.0359 1.0000 0.0309
-7.500 -0.4064 0.07740 0.07277 -0.0354 1.0000 0.0303
-7.250 -0.4137 0.07407 0.06952 -0.0362 1.0000 0.0296
-7.000 -0.4208 0.07021 0.06570 -0.0376 1.0000 0.0288
-6.750 -0.4379 0.05831 0.05353 -0.0458 1.0000 0.0255
-6.500 -0.4362 0.05510 0.05026 -0.0455 1.0000 0.0253
-6.250 -0.4323 0.05162 0.04667 -0.0455 1.0000 0.0250
-6.000 -0.4260 0.04769 0.04255 -0.0458 1.0000 0.0247
-5.750 -0.4007 0.04230 0.03673 -0.0501 0.9957 0.0243
-5.500 -0.3709 0.03712 0.03098 -0.0541 0.9904 0.0240
-5.250 -0.3383 0.03280 0.02603 -0.0573 0.9858 0.0240
-5.000 -0.3064 0.02942 0.02202 -0.0593 0.9809 0.0242
-4.750 -0.2723 0.02685 0.01877 -0.0611 0.9761 0.0254
-4.500 -0.2373 0.02509 0.01680 -0.0632 0.9721 0.0271
-4.250 -0.2063 0.02352 0.01496 -0.0641 0.9660 0.0281
-4.000 -0.1709 0.02201 0.01320 -0.0656 0.9614 0.0294
-3.750 -0.1367 0.02078 0.01176 -0.0668 0.9564 0.0307
-3.500 -0.1043 0.01971 0.01056 -0.0676 0.9500 0.0327
-3.250 -0.0669 0.01889 0.00973 -0.0697 0.9455 0.0380
-3.000 -0.0364 0.01812 0.00888 -0.0703 0.9379 0.0447
-2.750 0.0000 0.01724 0.00799 -0.0719 0.9324 0.0637
-2.500 0.0318 0.01634 0.00750 -0.0730 0.9254 0.1361
-2.250 0.0635 0.01544 0.00722 -0.0742 0.9183 0.2743
-2.000 0.0943 0.01477 0.00699 -0.0748 0.9109 0.4076
-1.750 0.1228 0.01413 0.00687 -0.0746 0.9029 0.5627
-1.500 0.1473 0.01366 0.00679 -0.0730 0.8938 0.7016
-1.250 0.1749 0.01328 0.00664 -0.0716 0.8862 0.8240
-1.000 0.2211 0.01297 0.00634 -0.0743 0.8784 0.9529
-0.750 0.2640 0.01280 0.00597 -0.0771 0.8705 1.0000
-0.500 0.2911 0.01276 0.00577 -0.0767 0.8578 1.0000
-0.250 0.3190 0.01272 0.00558 -0.0765 0.8451 1.0000
0.000 0.3472 0.01268 0.00540 -0.0763 0.8322 1.0000
0.250 0.3756 0.01264 0.00524 -0.0761 0.8188 1.0000
0.500 0.4038 0.01261 0.00509 -0.0758 0.8045 1.0000
0.750 0.4319 0.01258 0.00496 -0.0755 0.7894 1.0000
1.000 0.4600 0.01258 0.00485 -0.0752 0.7735 1.0000
1.250 0.4879 0.01258 0.00475 -0.0748 0.7569 1.0000
1.500 0.5158 0.01261 0.00468 -0.0744 0.7395 1.0000
2.000 0.5700 0.01277 0.00464 -0.0735 0.7018 1.0000
2.250 0.5966 0.01288 0.00467 -0.0729 0.6817 1.0000
2.750 0.6491 0.01320 0.00480 -0.0718 0.6402 1.0000
3.000 0.6750 0.01340 0.00490 -0.0712 0.6190 1.0000
3.250 0.7005 0.01362 0.00506 -0.0705 0.5973 1.0000
3.500 0.7259 0.01387 0.00523 -0.0699 0.5752 1.0000
3.750 0.7510 0.01413 0.00542 -0.0692 0.5532 1.0000
4.000 0.7758 0.01442 0.00566 -0.0685 0.5306 1.0000
4.250 0.8004 0.01472 0.00590 -0.0679 0.5083 1.0000
4.500 0.8248 0.01505 0.00617 -0.0671 0.4856 1.0000
4.750 0.8489 0.01540 0.00646 -0.0664 0.4630 1.0000
5.000 0.8728 0.01577 0.00681 -0.0657 0.4403 1.0000
5.250 0.8964 0.01617 0.00717 -0.0649 0.4176 1.0000
5.500 0.9197 0.01659 0.00755 -0.0641 0.3951 1.0000
5.750 0.9428 0.01704 0.00797 -0.0633 0.3727 1.0000
6.000 0.9654 0.01752 0.00844 -0.0625 0.3507 1.0000
6.250 0.9879 0.01802 0.00893 -0.0617 0.3289 1.0000
6.500 1.0100 0.01855 0.00945 -0.0608 0.3077 1.0000
6.750 1.0315 0.01913 0.01002 -0.0599 0.2873 1.0000
7.000 1.0531 0.01971 0.01062 -0.0590 0.2672 1.0000
7.250 1.0739 0.02035 0.01126 -0.0580 0.2479 1.0000
7.500 1.0942 0.02103 0.01193 -0.0570 0.2298 1.0000
7.750 1.1144 0.02171 0.01268 -0.0560 0.2115 1.0000
8.000 1.1339 0.02244 0.01344 -0.0549 0.1941 1.0000
8.250 1.1527 0.02322 0.01425 -0.0538 0.1778 1.0000
8.500 1.1708 0.02405 0.01512 -0.0525 0.1624 1.0000
8.750 1.1882 0.02492 0.01604 -0.0513 0.1481 1.0000
9.000 1.2049 0.02584 0.01704 -0.0499 0.1346 1.0000
9.250 1.2204 0.02682 0.01809 -0.0484 0.1212 1.0000
9.500 1.2340 0.02787 0.01913 -0.0469 0.1061 1.0000
9.750 1.2478 0.02890 0.02022 -0.0454 0.0881 1.0000
10.000 1.2585 0.03010 0.02138 -0.0436 0.0722 1.0000
10.250 1.2671 0.03138 0.02271 -0.0415 0.0613 1.0000
10.500 1.2738 0.03284 0.02426 -0.0393 0.0521 1.0000
10.750 1.2776 0.03454 0.02603 -0.0369 0.0449 1.0000
11.000 1.2776 0.03656 0.02810 -0.0346 0.0393 1.0000
11.250 1.2787 0.03861 0.03031 -0.0325 0.0348 1.0000
11.500 1.2766 0.04097 0.03275 -0.0306 0.0318 1.0000
11.750 1.2741 0.04352 0.03545 -0.0291 0.0294 1.0000
12.000 1.2723 0.04617 0.03828 -0.0280 0.0273 1.0000
12.250 1.2689 0.04909 0.04134 -0.0273 0.0256 1.0000
12.500 1.2634 0.05243 0.04481 -0.0270 0.0247 1.0000
12.750 1.2567 0.05612 0.04863 -0.0271 0.0239 1.0000
13.000 1.2522 0.05982 0.05256 -0.0274 0.0232 1.0000
13.250 1.2468 0.06380 0.05675 -0.0280 0.0225 1.0000
13.500 1.2409 0.06801 0.06115 -0.0290 0.0220 1.0000
13.750 1.2342 0.07254 0.06586 -0.0303 0.0215 1.0000
14.000 1.2272 0.07724 0.07075 -0.0318 0.0212 1.0000
14.250 1.2191 0.08232 0.07601 -0.0338 0.0208 1.0000
14.500 1.2102 0.08775 0.08161 -0.0361 0.0205 1.0000
14.750 1.2011 0.09340 0.08745 -0.0386 0.0203 1.0000
15.000 1.1911 0.09945 0.09367 -0.0415 0.0201 1.0000
15.250 1.1802 0.10590 0.10029 -0.0448 0.0200 1.0000
15.500 1.1683 0.11282 0.10739 -0.0486 0.0199 1.0000
15.750 1.1548 0.12043 0.11518 -0.0529 0.0198 1.0000
16.000 1.1389 0.12900 0.12394 -0.0580 0.0199 1.0000
16.250 1.1179 0.13944 0.13459 -0.0644 0.0201 1.0000
16.500 1.0881 0.15333 0.14869 -0.0729 0.0206 1.0000
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Polar data table (+)
Polar graphs
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