GOE 744 AIRFOIL (goe744-il) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 744 AIRFOIL (goe744-il) Reynolds number: 500,000 Max Cl/Cd: 97.29 at α=6.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe744-il-500000-n5.txt Download as CSV file: xf-goe744-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 744 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.2102 0.09041 0.08636 -0.0009 0.4846 0.0269
-7.750 -0.2079 0.08730 0.08325 -0.0025 0.4831 0.0269
-7.500 -0.2075 0.08425 0.08021 -0.0041 0.4813 0.0269
-7.250 -0.2092 0.08138 0.07734 -0.0052 0.4798 0.0269
-7.000 -0.2062 0.07856 0.07451 -0.0064 0.4780 0.0269
-6.750 -0.2021 0.07490 0.07083 -0.0088 0.4767 0.0269
-6.500 -0.1931 0.07186 0.06777 -0.0104 0.4754 0.0269
-6.250 -0.1807 0.06972 0.06565 -0.0109 0.4737 0.0272
-6.000 -0.1662 0.06767 0.06358 -0.0114 0.4718 0.0266
-5.750 -0.1526 0.06525 0.06115 -0.0124 0.4697 0.0262
-5.500 -0.1395 0.06213 0.05799 -0.0140 0.4678 0.0257
-5.250 -0.1254 0.05863 0.05442 -0.0159 0.4660 0.0255
-5.000 -0.1096 0.05507 0.05077 -0.0176 0.4643 0.0253
-4.750 -0.0923 0.05149 0.04708 -0.0192 0.4625 0.0251
-4.500 -0.0739 0.04783 0.04330 -0.0205 0.4607 0.0251
-4.250 -0.0546 0.04407 0.03938 -0.0215 0.4587 0.0251
-4.000 -0.0343 0.04032 0.03549 -0.0221 0.4572 0.0254
-3.500 -0.0197 0.01933 0.01252 -0.0185 0.4553 0.0265
-3.250 0.0054 0.01785 0.01068 -0.0178 0.4532 0.0268
-3.000 0.0320 0.01694 0.00959 -0.0173 0.4509 0.0271
-2.750 0.0595 0.01648 0.00906 -0.0171 0.4483 0.0274
-2.500 0.0874 0.01614 0.00866 -0.0169 0.4457 0.0277
-2.250 0.1154 0.01581 0.00824 -0.0166 0.4432 0.0280
-2.000 0.1434 0.01544 0.00777 -0.0164 0.4409 0.0284
-1.750 0.1717 0.01498 0.00725 -0.0162 0.4389 0.0288
-1.500 0.2001 0.01455 0.00674 -0.0160 0.4362 0.0292
-1.250 0.2285 0.01417 0.00628 -0.0158 0.4334 0.0296
-1.000 0.2570 0.01382 0.00587 -0.0157 0.4306 0.0301
-0.750 0.2855 0.01354 0.00551 -0.0155 0.4280 0.0305
-0.500 0.3137 0.01327 0.00519 -0.0154 0.4253 0.0309
-0.250 0.3420 0.01307 0.00499 -0.0152 0.4227 0.0313
0.000 0.3705 0.01289 0.00484 -0.0151 0.4199 0.0319
0.250 0.3989 0.01274 0.00469 -0.0150 0.4170 0.0325
0.500 0.4272 0.01261 0.00455 -0.0149 0.4137 0.0334
0.750 0.4554 0.01251 0.00440 -0.0148 0.4105 0.0344
1.000 0.4833 0.01239 0.00427 -0.0146 0.4074 0.0352
1.250 0.5115 0.01229 0.00420 -0.0145 0.4046 0.0361
1.500 0.5396 0.01220 0.00414 -0.0144 0.4011 0.0371
1.750 0.5675 0.01214 0.00407 -0.0143 0.3974 0.0383
2.000 0.5953 0.01209 0.00401 -0.0142 0.3938 0.0396
2.250 0.6229 0.01209 0.00400 -0.0141 0.3904 0.0414
2.500 0.6509 0.01207 0.00400 -0.0140 0.3872 0.0437
2.750 0.6785 0.01204 0.00401 -0.0139 0.3837 0.0466
3.000 0.7061 0.01206 0.00402 -0.0138 0.3800 0.0496
3.250 0.7333 0.01209 0.00404 -0.0136 0.3761 0.0540
3.500 0.7605 0.01210 0.00408 -0.0135 0.3727 0.0623
3.750 0.7863 0.01198 0.00418 -0.0132 0.3691 0.1325
4.000 0.8128 0.01199 0.00433 -0.0130 0.3654 0.1964
4.250 0.8396 0.01208 0.00445 -0.0129 0.3617 0.2203
4.500 0.8658 0.01215 0.00458 -0.0127 0.3583 0.2527
4.750 0.8847 0.01164 0.00473 -0.0113 0.3551 0.5439
5.500 1.0738 0.01173 0.00569 -0.0333 0.3395 0.9923
5.750 1.1089 0.01191 0.00585 -0.0350 0.3354 0.9940
6.000 1.1443 0.01212 0.00603 -0.0369 0.3312 0.9958
6.250 1.1803 0.01237 0.00624 -0.0390 0.3271 0.9979
6.500 1.2156 0.01255 0.00642 -0.0408 0.3234 0.9995
6.750 1.2444 0.01279 0.00665 -0.0414 0.3193 1.0000
7.000 1.2686 0.01309 0.00693 -0.0412 0.3151 1.0000
7.250 1.2922 0.01343 0.00724 -0.0409 0.3112 1.0000
7.500 1.3163 0.01368 0.00752 -0.0406 0.3078 1.0000
7.750 1.3397 0.01399 0.00783 -0.0403 0.3041 1.0000
8.000 1.3622 0.01435 0.00819 -0.0399 0.3005 1.0000
8.250 1.3836 0.01479 0.00861 -0.0394 0.2969 1.0000
8.500 1.4053 0.01515 0.00899 -0.0389 0.2940 1.0000
8.750 1.4265 0.01553 0.00940 -0.0384 0.2908 1.0000
9.000 1.4461 0.01598 0.00988 -0.0377 0.2874 1.0000
9.250 1.4636 0.01655 0.01045 -0.0369 0.2840 1.0000
9.500 1.4780 0.01728 0.01117 -0.0359 0.2806 1.0000
9.750 1.4934 0.01793 0.01188 -0.0350 0.2778 1.0000
10.000 1.5032 0.01896 0.01296 -0.0341 0.2745 1.0000
10.250 1.4970 0.02028 0.01432 -0.0309 0.2718 1.0000
10.500 1.4949 0.02166 0.01572 -0.0285 0.2690 1.0000
10.750 1.4943 0.02319 0.01726 -0.0266 0.2662 1.0000
11.000 1.4984 0.02455 0.01864 -0.0252 0.2638 1.0000
11.250 1.5051 0.02580 0.01994 -0.0241 0.2615 1.0000
11.500 1.5103 0.02721 0.02141 -0.0230 0.2589 1.0000
11.750 1.5136 0.02883 0.02305 -0.0220 0.2561 1.0000
12.000 1.5151 0.03062 0.02486 -0.0210 0.2532 1.0000
12.250 1.5151 0.03258 0.02682 -0.0201 0.2502 1.0000
12.500 1.5207 0.03414 0.02844 -0.0194 0.2481 1.0000
12.750 1.5263 0.03573 0.03009 -0.0188 0.2460 1.0000
13.000 1.5309 0.03743 0.03184 -0.0182 0.2436 1.0000
13.250 1.5341 0.03931 0.03375 -0.0177 0.2411 1.0000
13.500 1.5372 0.04124 0.03571 -0.0173 0.2386 1.0000
13.750 1.5382 0.04341 0.03788 -0.0169 0.2357 1.0000
14.000 1.5424 0.04536 0.03989 -0.0167 0.2330 1.0000
14.250 1.5463 0.04739 0.04198 -0.0165 0.2300 1.0000
14.500 1.5479 0.04968 0.04431 -0.0164 0.2266 1.0000
14.750 1.5485 0.05207 0.04670 -0.0162 0.2231 1.0000
15.000 1.5484 0.05453 0.04917 -0.0161 0.2200 1.0000
15.250 1.5526 0.05666 0.05138 -0.0162 0.2171 1.0000
15.500 1.5558 0.05889 0.05367 -0.0162 0.2147 1.0000
15.750 1.5572 0.06131 0.05614 -0.0163 0.2116 1.0000
16.000 1.5579 0.06382 0.05866 -0.0163 0.2084 1.0000
16.250 1.5573 0.06650 0.06135 -0.0165 0.2055 1.0000
16.500 1.5606 0.06882 0.06376 -0.0167 0.2030 1.0000
16.750 1.5610 0.07149 0.06649 -0.0169 0.1996 1.0000
17.000 1.5610 0.07420 0.06925 -0.0172 0.1969 1.0000
17.250 1.5620 0.07680 0.07187 -0.0175 0.1942 1.0000
17.500 1.5607 0.07968 0.07478 -0.0179 0.1913 1.0000
17.750 1.5610 0.08246 0.07765 -0.0183 0.1884 1.0000
18.000 1.5621 0.08512 0.08038 -0.0187 0.1856 1.0000
18.250 1.5564 0.08869 0.08399 -0.0193 0.1817 1.0000
18.500 1.5527 0.09199 0.08730 -0.0200 0.1780 1.0000
18.750 1.5497 0.09527 0.09067 -0.0206 0.1745 1.0000
19.000 1.5450 0.09879 0.09423 -0.0214 0.1702 1.0000
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