YS-900 (ys900-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: YS-900 (ys900-il) Reynolds number: 200,000 Max Cl/Cd: 21.5 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-ys900-il-200000.txt Download as CSV file: xf-ys900-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: YS-900
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.500 -0.5098 0.09437 0.09130 -0.0244 1.0000 0.0287
-9.250 -0.5177 0.09005 0.08701 -0.0252 1.0000 0.0289
-9.000 -0.5280 0.08540 0.08239 -0.0263 1.0000 0.0291
-8.750 -0.5442 0.08000 0.07701 -0.0291 1.0000 0.0286
-8.500 -0.5669 0.07501 0.07199 -0.0307 1.0000 0.0278
-8.250 -0.5934 0.07124 0.06817 -0.0292 1.0000 0.0271
-8.000 -0.6226 0.06911 0.06595 -0.0245 1.0000 0.0265
-7.750 -0.6416 0.06650 0.06329 -0.0199 1.0000 0.0266
-7.500 -0.6523 0.06318 0.05994 -0.0165 1.0000 0.0271
-7.250 -0.7204 0.07422 0.07035 -0.0057 1.0000 0.0254
-7.000 -0.7331 0.06799 0.06408 -0.0026 1.0000 0.0261
-6.750 -0.7366 0.06386 0.05995 0.0001 1.0000 0.0270
-6.500 -0.7381 0.06077 0.05680 0.0033 1.0000 0.0279
-6.250 -0.7386 0.05782 0.05374 0.0067 1.0000 0.0291
-6.000 -0.7373 0.05500 0.05076 0.0102 1.0000 0.0305
-5.750 -0.7343 0.05216 0.04772 0.0138 1.0000 0.0323
-5.500 -0.7281 0.04968 0.04496 0.0177 1.0000 0.0350
-5.000 -0.7190 0.04401 0.03858 0.0263 1.0000 0.0394
-4.750 -0.7104 0.04096 0.03551 0.0286 1.0000 0.0419
-4.500 -0.6993 0.03891 0.03322 0.0317 1.0000 0.0467
-4.250 -0.6902 0.03660 0.03045 0.0357 1.0000 0.0527
-4.000 -0.6764 0.03429 0.02800 0.0378 1.0000 0.0586
-3.750 -0.6637 0.03214 0.02559 0.0405 1.0000 0.0686
-3.500 -0.6496 0.03030 0.02356 0.0428 1.0000 0.0826
-3.250 -0.6369 0.02849 0.02158 0.0452 1.0000 0.1069
-2.500 -0.5407 0.02238 0.01405 0.0512 1.0000 0.0353
-2.250 -0.5128 0.02160 0.01299 0.0529 1.0000 0.0253
-2.000 -0.4843 0.01925 0.01058 0.0532 1.0000 0.0220
-1.750 -0.4623 0.01800 0.00927 0.0549 1.0000 0.0196
-1.500 -0.0943 0.01853 0.01243 -0.0111 1.0000 1.0000
-1.250 -0.0788 0.01841 0.01226 -0.0092 1.0000 1.0000
-1.000 -0.0631 0.01831 0.01210 -0.0074 1.0000 1.0000
-0.750 -0.0474 0.01824 0.01198 -0.0055 1.0000 1.0000
-0.500 -0.0316 0.01819 0.01190 -0.0037 1.0000 1.0000
-0.250 -0.0158 0.01816 0.01185 -0.0019 1.0000 1.0000
0.000 0.0000 0.01815 0.01183 0.0000 1.0000 1.0000
0.250 0.0158 0.01816 0.01185 0.0018 1.0000 1.0000
0.500 0.0317 0.01819 0.01190 0.0036 1.0000 1.0000
0.750 0.0474 0.01825 0.01198 0.0055 1.0000 1.0000
1.000 0.0631 0.01832 0.01210 0.0073 1.0000 1.0000
1.250 0.0787 0.01841 0.01225 0.0092 1.0000 1.0000
1.500 0.0942 0.01853 0.01243 0.0110 1.0000 1.0000
1.750 0.1095 0.01868 0.01265 0.0129 1.0000 1.0000
3.500 0.6510 0.03028 0.02350 -0.0434 0.0856 1.0000
3.750 0.6650 0.03193 0.02538 -0.0409 0.0701 1.0000
4.000 0.6775 0.03444 0.02809 -0.0383 0.0605 1.0000
4.250 0.6919 0.03617 0.03005 -0.0359 0.0533 1.0000
4.500 0.7001 0.03907 0.03330 -0.0323 0.0481 1.0000
4.750 0.7123 0.04068 0.03523 -0.0290 0.0427 1.0000
5.000 0.7210 0.04356 0.03816 -0.0265 0.0398 1.0000
5.500 0.7272 0.05030 0.04546 -0.0185 0.0364 1.0000
5.750 0.7362 0.05192 0.04746 -0.0142 0.0328 1.0000
6.000 0.7395 0.05473 0.05048 -0.0106 0.0310 1.0000
6.250 0.7407 0.05760 0.05351 -0.0070 0.0294 1.0000
6.500 0.7404 0.06052 0.05656 -0.0035 0.0282 1.0000
6.750 0.7388 0.06353 0.05964 -0.0003 0.0273 1.0000
7.000 0.7355 0.06724 0.06337 0.0026 0.0264 1.0000
7.250 0.7260 0.07294 0.06908 0.0055 0.0256 1.0000
7.500 0.7119 0.07860 0.07480 0.0089 0.0252 1.0000
7.750 0.7036 0.08137 0.07769 0.0126 0.0252 1.0000
8.000 0.6931 0.08415 0.08058 0.0163 0.0251 1.0000
8.250 0.6818 0.08686 0.08338 0.0197 0.0251 1.0000
8.500 0.6653 0.08917 0.08574 0.0239 0.0251 1.0000
8.750 0.6480 0.09124 0.08785 0.0277 0.0251 1.0000
9.000 0.6313 0.09387 0.09051 0.0303 0.0251 1.0000
9.250 0.6169 0.09702 0.09370 0.0314 0.0251 1.0000
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Polar data table (+)
Polar graphs
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