WASP (smoothed) (waspsm-il) Xfoil prediction polar at RE=100,000 Ncrit=5
| Details | Polar file |
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Airfoil: WASP (smoothed) (waspsm-il) Reynolds number: 100,000 Max Cl/Cd: 53.22 at α=6.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-waspsm-il-100000-n5.txt Download as CSV file: xf-waspsm-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: WASP (smoothed)
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 -0.4421 0.08268 0.07774 -0.0321 1.0000 0.0306
-8.000 -0.4443 0.07900 0.07411 -0.0332 1.0000 0.0304
-7.750 -0.4448 0.07472 0.06988 -0.0356 1.0000 0.0302
-7.500 -0.4451 0.06987 0.06507 -0.0387 1.0000 0.0299
-7.250 -0.4448 0.06439 0.05957 -0.0421 1.0000 0.0297
-7.000 -0.4444 0.05836 0.05346 -0.0452 1.0000 0.0295
-6.750 -0.4436 0.05226 0.04719 -0.0473 1.0000 0.0293
-6.500 -0.4416 0.04642 0.04107 -0.0483 1.0000 0.0293
-6.250 -0.4376 0.04074 0.03489 -0.0485 1.0000 0.0299
-6.000 -0.4297 0.03601 0.02952 -0.0478 1.0000 0.0310
-5.750 -0.4156 0.03431 0.02773 -0.0468 1.0000 0.0323
-5.500 -0.4004 0.03230 0.02548 -0.0456 1.0000 0.0334
-5.250 -0.3840 0.02978 0.02255 -0.0445 1.0000 0.0343
-5.000 -0.3657 0.02754 0.01988 -0.0434 1.0000 0.0355
-4.750 -0.3349 0.02542 0.01722 -0.0444 0.9968 0.0383
-4.500 -0.2995 0.02359 0.01505 -0.0463 0.9910 0.0414
-4.250 -0.2639 0.02220 0.01347 -0.0481 0.9844 0.0441
-4.000 -0.2267 0.02101 0.01201 -0.0500 0.9781 0.0486
-3.750 -0.1917 0.01987 0.01077 -0.0516 0.9707 0.0533
-3.500 -0.1539 0.01891 0.00971 -0.0536 0.9645 0.0588
-3.250 -0.1182 0.01811 0.00887 -0.0552 0.9566 0.0672
-3.000 -0.0811 0.01736 0.00807 -0.0570 0.9496 0.0777
-2.750 -0.0446 0.01671 0.00744 -0.0588 0.9416 0.0940
-2.500 -0.0098 0.01613 0.00689 -0.0601 0.9322 0.1184
-2.250 0.0266 0.01550 0.00644 -0.0618 0.9237 0.1591
-2.000 0.0584 0.01494 0.00610 -0.0626 0.9119 0.2217
-1.750 0.0897 0.01436 0.00586 -0.0633 0.8996 0.3152
-1.500 0.1214 0.01374 0.00570 -0.0640 0.8873 0.4467
-1.250 0.1519 0.01312 0.00554 -0.0641 0.8744 0.5953
-1.000 0.2322 0.01203 0.00524 -0.0739 0.8679 1.0000
-0.750 0.2649 0.01200 0.00498 -0.0746 0.8514 1.0000
-0.500 0.2960 0.01199 0.00478 -0.0750 0.8337 1.0000
-0.250 0.3259 0.01201 0.00461 -0.0750 0.8148 1.0000
0.000 0.3556 0.01204 0.00446 -0.0750 0.7956 1.0000
0.250 0.3851 0.01209 0.00433 -0.0750 0.7763 1.0000
0.500 0.4127 0.01217 0.00426 -0.0746 0.7555 1.0000
0.750 0.4402 0.01227 0.00420 -0.0742 0.7349 1.0000
1.000 0.4672 0.01240 0.00417 -0.0737 0.7145 1.0000
1.250 0.4932 0.01254 0.00418 -0.0730 0.6931 1.0000
1.500 0.5193 0.01270 0.00420 -0.0724 0.6725 1.0000
1.750 0.5448 0.01288 0.00425 -0.0716 0.6515 1.0000
2.000 0.5701 0.01307 0.00432 -0.0709 0.6308 1.0000
2.250 0.5953 0.01328 0.00440 -0.0701 0.6108 1.0000
2.500 0.6202 0.01350 0.00454 -0.0693 0.5905 1.0000
2.750 0.6449 0.01374 0.00467 -0.0685 0.5711 1.0000
3.000 0.6696 0.01400 0.00482 -0.0677 0.5524 1.0000
3.250 0.6941 0.01426 0.00500 -0.0669 0.5337 1.0000
3.500 0.7185 0.01453 0.00523 -0.0660 0.5154 1.0000
3.750 0.7427 0.01482 0.00545 -0.0652 0.4976 1.0000
4.000 0.7669 0.01512 0.00569 -0.0644 0.4804 1.0000
4.250 0.7910 0.01544 0.00595 -0.0635 0.4638 1.0000
4.500 0.8149 0.01576 0.00626 -0.0627 0.4474 1.0000
4.750 0.8387 0.01610 0.00656 -0.0619 0.4317 1.0000
5.000 0.8625 0.01644 0.00690 -0.0610 0.4158 1.0000
5.250 0.8861 0.01680 0.00726 -0.0602 0.4003 1.0000
5.500 0.9095 0.01717 0.00766 -0.0593 0.3851 1.0000
5.750 0.9328 0.01756 0.00806 -0.0585 0.3700 1.0000
6.000 0.9559 0.01797 0.00849 -0.0576 0.3552 1.0000
6.250 0.9788 0.01839 0.00894 -0.0566 0.3406 1.0000
6.500 1.0014 0.01884 0.00945 -0.0557 0.3264 1.0000
6.750 1.0237 0.01931 0.00996 -0.0547 0.3124 1.0000
7.000 1.0458 0.01981 0.01050 -0.0537 0.2988 1.0000
7.250 1.0678 0.02032 0.01108 -0.0528 0.2853 1.0000
7.500 1.0894 0.02086 0.01172 -0.0517 0.2720 1.0000
7.750 1.1103 0.02142 0.01235 -0.0506 0.2579 1.0000
8.000 1.1295 0.02200 0.01293 -0.0493 0.2403 1.0000
8.250 1.1483 0.02257 0.01356 -0.0480 0.2185 1.0000
8.500 1.1658 0.02325 0.01425 -0.0465 0.1985 1.0000
8.750 1.1839 0.02395 0.01501 -0.0452 0.1792 1.0000
9.000 1.2007 0.02475 0.01583 -0.0437 0.1588 1.0000
9.250 1.2164 0.02565 0.01675 -0.0422 0.1364 1.0000
9.500 1.2298 0.02676 0.01782 -0.0404 0.1091 1.0000
9.750 1.2391 0.02823 0.01914 -0.0382 0.0805 1.0000
10.000 1.2453 0.02993 0.02076 -0.0357 0.0625 1.0000
10.250 1.2493 0.03168 0.02248 -0.0330 0.0531 1.0000
10.500 1.2518 0.03333 0.02422 -0.0300 0.0469 1.0000
10.750 1.2513 0.03520 0.02615 -0.0270 0.0429 1.0000
11.000 1.2525 0.03702 0.02813 -0.0245 0.0396 1.0000
11.250 1.2513 0.03912 0.03037 -0.0223 0.0374 1.0000
11.500 1.2470 0.04162 0.03297 -0.0204 0.0358 1.0000
11.750 1.2414 0.04444 0.03589 -0.0190 0.0345 1.0000
12.000 1.2403 0.04706 0.03871 -0.0180 0.0332 1.0000
12.250 1.2383 0.04992 0.04175 -0.0173 0.0318 1.0000
12.500 1.2354 0.05302 0.04500 -0.0170 0.0304 1.0000
12.750 1.2316 0.05636 0.04849 -0.0171 0.0292 1.0000
13.000 1.2268 0.05995 0.05219 -0.0175 0.0283 1.0000
13.250 1.2213 0.06370 0.05603 -0.0179 0.0274 1.0000
13.500 1.2172 0.06727 0.05965 -0.0179 0.0268 1.0000
13.750 1.2148 0.07089 0.06347 -0.0182 0.0262 1.0000
14.000 1.2114 0.07472 0.06749 -0.0188 0.0257 1.0000
14.250 1.2066 0.07883 0.07180 -0.0195 0.0253 1.0000
14.500 1.2007 0.08321 0.07637 -0.0206 0.0248 1.0000
14.750 1.1931 0.08800 0.08136 -0.0221 0.0244 1.0000
15.000 1.1839 0.09322 0.08677 -0.0240 0.0241 1.0000
15.250 1.1734 0.09887 0.09261 -0.0264 0.0238 1.0000
15.500 1.1614 0.10498 0.09890 -0.0292 0.0235 1.0000
15.750 1.1480 0.11161 0.10572 -0.0326 0.0233 1.0000
16.000 1.1331 0.11888 0.11318 -0.0365 0.0232 1.0000
16.250 1.1160 0.12703 0.12151 -0.0411 0.0232 1.0000
16.500 1.0953 0.13648 0.13114 -0.0466 0.0234 1.0000
16.750 1.0675 0.14866 0.14350 -0.0540 0.0240 1.0000
17.000 1.0311 0.16487 0.15984 -0.0636 0.0248 1.0000
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