GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il) Xfoil prediction polar at RE=500,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 417A (GEW. PLATTE) AIRFOIL (goe417a-il) Reynolds number: 500,000 Max Cl/Cd: 75.9 at α=5.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe417a-il-500000.txt Download as CSV file: xf-goe417a-il-500000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 417A (GEW. PLATTE) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3693 0.11571 0.11341 -0.0135 1.0000 0.0156
-9.000 -0.3706 0.11417 0.11189 -0.0129 1.0000 0.0157
-8.750 -0.3719 0.11254 0.11028 -0.0121 1.0000 0.0157
-8.000 -0.3712 0.10577 0.10357 -0.0112 0.9989 0.0158
-7.750 -0.3564 0.10186 0.09966 -0.0138 0.9969 0.0159
-7.500 -0.3395 0.09848 0.09627 -0.0176 0.9945 0.0161
-7.250 -0.3224 0.09527 0.09305 -0.0212 0.9913 0.0164
-7.000 -0.3025 0.09189 0.08966 -0.0254 0.9882 0.0168
-6.750 -0.2787 0.08833 0.08608 -0.0306 0.9856 0.0172
-6.500 -0.2526 0.08482 0.08256 -0.0362 0.9838 0.0177
-6.250 -0.2330 0.08188 0.07960 -0.0398 0.9800 0.0182
-6.000 -0.2090 0.07895 0.07664 -0.0444 0.9763 0.0184
-5.750 -0.1751 0.07579 0.07343 -0.0518 0.9735 0.0186
-5.500 -0.1328 0.07262 0.07019 -0.0614 0.9715 0.0186
-2.750 0.2436 0.02181 0.01899 -0.1054 0.9362 0.0220
-2.500 0.2656 0.01897 0.01616 -0.1064 0.9316 0.0222
-2.250 0.2947 0.01656 0.01371 -0.1087 0.9286 0.0224
-2.000 0.3274 0.01451 0.01160 -0.1113 0.9260 0.0228
-1.750 0.3469 0.01336 0.01040 -0.1106 0.9180 0.0233
-1.500 0.3783 0.01179 0.00874 -0.1122 0.9127 0.0240
-1.250 0.4043 0.01067 0.00754 -0.1124 0.9051 0.0249
-1.000 0.4418 0.01020 0.00685 -0.1132 0.8981 0.0257
-0.750 0.4693 0.00945 0.00595 -0.1129 0.8894 0.0258
-0.500 0.4925 0.00789 0.00432 -0.1130 0.8806 0.0260
-0.250 0.5281 0.02176 0.01796 -0.1176 0.8924 0.0261
0.000 0.5504 0.02034 0.01650 -0.1170 0.8817 0.0264
0.250 0.5732 0.01921 0.01530 -0.1160 0.8688 0.0268
0.500 0.5986 0.01815 0.01415 -0.1154 0.8528 0.0274
0.750 0.6254 0.01717 0.01303 -0.1149 0.8331 0.0283
1.000 0.6533 0.01641 0.01205 -0.1141 0.8038 0.0298
1.250 0.6832 0.01649 0.01173 -0.1127 0.7669 0.0306
1.500 0.7013 0.01493 0.00996 -0.1112 0.7346 0.0314
1.750 0.7215 0.01441 0.00927 -0.1096 0.7074 0.0323
2.000 0.7428 0.01402 0.00870 -0.1080 0.6823 0.0340
2.250 0.7679 0.01463 0.00903 -0.1062 0.6577 0.0367
2.500 0.7858 0.01331 0.00758 -0.1043 0.6315 0.0380
2.750 0.8046 0.01302 0.00712 -0.1024 0.5978 0.0393
3.000 0.8240 0.01288 0.00679 -0.1004 0.5665 0.0414
5.500 1.0232 0.01354 0.00528 -0.0831 0.1810 0.0459
5.750 1.0436 0.01375 0.00541 -0.0816 0.1602 0.0442
6.000 1.0576 0.01440 0.00562 -0.0790 0.0795 0.0439
6.250 1.0705 0.01521 0.00624 -0.0761 0.0444 0.0444
6.500 1.0893 0.01549 0.00659 -0.0743 0.0402 0.0456
6.750 1.1048 0.01612 0.00725 -0.0718 0.0350 0.0511
7.000 1.1233 0.01648 0.00765 -0.0699 0.0333 0.0544
7.250 1.1405 0.01691 0.00814 -0.0678 0.0313 0.0713
7.500 1.2962 0.01889 0.01143 -0.0985 0.0249 1.0000
7.750 1.3114 0.01958 0.01216 -0.0960 0.0239 1.0000
8.000 1.3260 0.02028 0.01288 -0.0936 0.0228 1.0000
8.250 1.3386 0.02116 0.01380 -0.0908 0.0221 1.0000
8.500 1.3465 0.02264 0.01531 -0.0873 0.0212 1.0000
8.750 1.3591 0.02377 0.01651 -0.0845 0.0205 1.0000
9.000 1.3740 0.02442 0.01724 -0.0822 0.0199 1.0000
9.250 1.3868 0.02520 0.01809 -0.0795 0.0191 1.0000
9.500 1.3989 0.02615 0.01910 -0.0767 0.0186 1.0000
9.750 1.4106 0.02713 0.02017 -0.0739 0.0181 1.0000
10.000 1.4222 0.02817 0.02127 -0.0712 0.0176 1.0000
10.250 1.4331 0.02923 0.02238 -0.0685 0.0172 1.0000
10.500 1.4455 0.03067 0.02386 -0.0663 0.0166 1.0000
10.750 1.4744 0.03496 0.02834 -0.0678 0.0161 1.0000
11.000 1.4762 0.03570 0.02926 -0.0633 0.0159 1.0000
11.250 1.4773 0.03652 0.03026 -0.0588 0.0155 1.0000
11.500 1.4822 0.03846 0.03242 -0.0554 0.0153 1.0000
11.750 1.4831 0.03984 0.03397 -0.0515 0.0147 1.0000
12.000 1.4836 0.04214 0.03650 -0.0480 0.0146 1.0000
12.250 1.4799 0.04468 0.03928 -0.0441 0.0145 1.0000
12.500 1.4731 0.04733 0.04216 -0.0402 0.0144 1.0000
12.750 1.4639 0.04996 0.04501 -0.0364 0.0143 1.0000
13.000 1.4485 0.05363 0.04896 -0.0326 0.0144 1.0000
13.250 1.4343 0.05688 0.05242 -0.0296 0.0143 1.0000
13.500 1.4153 0.06100 0.05678 -0.0270 0.0144 1.0000
13.750 1.3965 0.06518 0.06117 -0.0253 0.0143 1.0000
14.000 1.3738 0.07035 0.06656 -0.0245 0.0146 1.0000
14.250 1.3510 0.07586 0.07227 -0.0248 0.0147 1.0000
14.500 1.3283 0.08179 0.07839 -0.0262 0.0148 1.0000
14.750 1.3050 0.08836 0.08514 -0.0285 0.0148 1.0000
15.000 1.2824 0.09548 0.09241 -0.0317 0.0150 1.0000
15.250 1.2576 0.10376 0.10084 -0.0361 0.0151 1.0000
15.500 1.2339 0.11256 0.10979 -0.0414 0.0152 1.0000
15.750 1.2113 0.12184 0.11918 -0.0470 0.0154 1.0000
16.000 1.1881 0.13199 0.12942 -0.0530 0.0158 1.0000
16.250 1.1778 0.14014 0.13768 -0.0575 0.0167 1.0000
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Polar data table (+)
Polar graphs
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