YS-930 (ys930-il) Xfoil prediction polar at RE=100,000 Ncrit=9
| Details | Polar file |
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Airfoil: YS-930 (ys930-il) Reynolds number: 100,000 Max Cl/Cd: 42.22 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ys930-il-100000.txt Download as CSV file: xf-ys930-il-100000.csv |
XFOIL Version 6.96
Calculated polar for: YS-930
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
------ -------- --------- --------- -------- -------- --------
-8.000 -0.4948 0.09796 0.09376 -0.0262 1.0000 0.1297
-7.750 -0.5209 0.09665 0.09255 -0.0249 1.0000 0.1326
-7.500 -0.5482 0.09520 0.09121 -0.0233 1.0000 0.1333
-7.250 -0.5672 0.09218 0.08825 -0.0250 1.0000 0.1337
-6.250 -0.5976 0.05151 0.04660 -0.0461 1.0000 0.0536
-6.000 -0.5872 0.04342 0.03726 -0.0481 1.0000 0.0446
-5.750 -0.5693 0.03976 0.03322 -0.0476 1.0000 0.0429
-5.500 -0.5500 0.03691 0.02972 -0.0472 1.0000 0.0436
-5.250 -0.5297 0.03337 0.02560 -0.0469 1.0000 0.0445
-5.000 -0.5077 0.02996 0.02182 -0.0464 1.0000 0.0460
-4.750 -0.4841 0.02765 0.01920 -0.0455 1.0000 0.0468
-4.500 -0.4605 0.02577 0.01713 -0.0445 1.0000 0.0498
-4.250 -0.4369 0.02445 0.01560 -0.0435 1.0000 0.0551
-4.000 -0.4139 0.02291 0.01405 -0.0428 1.0000 0.0669
-3.750 -0.3898 0.02136 0.01245 -0.0421 1.0000 0.0860
-3.500 -0.3664 0.02065 0.01242 -0.0416 1.0000 0.2583
-3.250 -0.3465 0.02112 0.01276 -0.0405 1.0000 0.2991
-3.000 -0.3271 0.02148 0.01312 -0.0394 1.0000 0.3342
-2.750 -0.3062 0.02151 0.01311 -0.0385 1.0000 0.3576
-2.500 -0.2838 0.02136 0.01283 -0.0378 1.0000 0.3718
-2.250 -0.2610 0.02118 0.01253 -0.0373 1.0000 0.3840
-2.000 -0.2382 0.02103 0.01223 -0.0368 1.0000 0.3962
-1.750 -0.2153 0.02090 0.01203 -0.0363 1.0000 0.4092
-1.500 -0.1926 0.02080 0.01191 -0.0357 1.0000 0.4232
-1.250 -0.1697 0.02071 0.01185 -0.0353 1.0000 0.4406
-1.000 -0.1467 0.02065 0.01183 -0.0349 1.0000 0.4631
-0.750 -0.1246 0.02057 0.01185 -0.0342 1.0000 0.4930
-0.500 -0.1012 0.02047 0.01201 -0.0338 1.0000 0.5460
-0.250 -0.0779 0.02006 0.01241 -0.0327 1.0000 0.7067
0.000 -0.0458 0.01960 0.01227 -0.0342 1.0000 1.0000
0.250 -0.0234 0.02000 0.01242 -0.0340 1.0000 1.0000
0.500 -0.0016 0.02041 0.01268 -0.0336 1.0000 1.0000
0.750 0.0198 0.02085 0.01299 -0.0333 1.0000 1.0000
1.000 0.0410 0.02131 0.01335 -0.0329 1.0000 1.0000
1.250 0.0818 0.02235 0.01429 -0.0364 0.9928 1.0000
1.500 0.1247 0.02344 0.01530 -0.0403 0.9841 1.0000
1.750 0.1603 0.02412 0.01594 -0.0428 0.9746 1.0000
2.000 0.1968 0.02489 0.01670 -0.0453 0.9656 1.0000
2.250 0.2389 0.02586 0.01766 -0.0488 0.9576 1.0000
2.500 0.2691 0.02631 0.01816 -0.0500 0.9475 1.0000
2.750 0.3012 0.02689 0.01879 -0.0516 0.9373 1.0000
3.000 0.3369 0.02753 0.01949 -0.0537 0.9272 1.0000
3.250 0.3806 0.02830 0.02035 -0.0572 0.9186 1.0000
3.500 0.4123 0.02871 0.02091 -0.0583 0.9066 1.0000
3.750 0.4459 0.02913 0.02147 -0.0598 0.8944 1.0000
4.000 0.4814 0.02951 0.02201 -0.0614 0.8819 1.0000
4.250 0.5198 0.02977 0.02247 -0.0633 0.8687 1.0000
4.500 0.5623 0.02980 0.02279 -0.0655 0.8546 1.0000
4.750 0.6211 0.02909 0.02244 -0.0694 0.8387 1.0000
5.000 0.7668 0.01816 0.01246 -0.0745 0.7408 1.0000
5.250 0.7668 0.02083 0.01089 -0.0648 0.0841 1.0000
5.500 0.7773 0.02238 0.01236 -0.0615 0.0613 1.0000
5.750 0.7928 0.02417 0.01414 -0.0589 0.0533 1.0000
6.000 0.8259 0.02651 0.01638 -0.0595 0.0476 1.0000
6.250 0.8670 0.02921 0.01922 -0.0611 0.0419 1.0000
6.500 0.9058 0.03203 0.02231 -0.0621 0.0402 1.0000
6.750 0.9394 0.03537 0.02605 -0.0620 0.0413 1.0000
7.000 0.9665 0.03934 0.03041 -0.0611 0.0436 1.0000
7.250 0.9898 0.04247 0.03418 -0.0585 0.0494 1.0000
11.250 0.7713 0.11697 0.11291 -0.0263 0.1227 1.0000
11.500 0.7323 0.12448 0.12038 -0.0336 0.1224 1.0000
11.750 0.6883 0.13038 0.12620 -0.0416 0.1193 1.0000
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Polar data table (+)
Polar graphs
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