GOE 427 AIRFOIL (goe427-il) Xfoil prediction polar at RE=100,000 Ncrit=5
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Airfoil: GOE 427 AIRFOIL (goe427-il) Reynolds number: 100,000 Max Cl/Cd: 67.07 at α=4° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe427-il-100000-n5.txt Download as CSV file: xf-goe427-il-100000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 427 AIRFOIL
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
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3260 0.10217 0.09750 -0.0240 1.0000 0.0303
-7.500 -0.3327 0.10101 0.09643 -0.0225 1.0000 0.0305
-7.250 -0.3361 0.09974 0.09524 -0.0225 1.0000 0.0307
-7.000 -0.3366 0.09800 0.09357 -0.0228 1.0000 0.0308
-6.750 -0.3355 0.09630 0.09192 -0.0238 1.0000 0.0309
-6.500 -0.3321 0.09434 0.09001 -0.0252 1.0000 0.0310
-6.250 -0.3265 0.09211 0.08781 -0.0267 1.0000 0.0311
-6.000 -0.3022 0.08840 0.08406 -0.0327 0.9967 0.0312
-5.750 -0.2716 0.08400 0.07960 -0.0394 0.9920 0.0313
-5.500 -0.2386 0.07934 0.07488 -0.0463 0.9875 0.0313
-5.250 -0.2261 0.07356 0.06915 -0.0469 0.9827 0.0319
-5.000 -0.2030 0.06893 0.06447 -0.0497 0.9784 0.0328
-4.750 -0.1746 0.06489 0.06038 -0.0542 0.9719 0.0337
-4.500 -0.1358 0.06055 0.05594 -0.0612 0.9673 0.0345
-4.250 -0.1005 0.05649 0.05177 -0.0671 0.9599 0.0347
-4.000 -0.0580 0.05256 0.04770 -0.0740 0.9554 0.0378
-3.500 0.0330 0.04321 0.03782 -0.0874 0.9433 0.0300
-3.250 0.0723 0.03919 0.03357 -0.0919 0.9382 0.0291
-3.000 0.1112 0.03529 0.02938 -0.0957 0.9324 0.0290
-2.750 0.1587 0.03058 0.02410 -0.1005 0.9292 0.0321
-2.500 0.1907 0.02826 0.02155 -0.1023 0.9235 0.0342
-2.250 0.2271 0.02532 0.01810 -0.1042 0.9183 0.0360
-2.000 0.2680 0.02292 0.01488 -0.1063 0.9149 0.0424
-1.750 0.2986 0.02093 0.01255 -0.1070 0.9086 0.0460
-1.500 0.3327 0.01991 0.01118 -0.1081 0.9031 0.0543
-1.250 0.3706 0.01847 0.00936 -0.1097 0.8996 0.0569
-1.000 0.3978 0.01765 0.00845 -0.1095 0.8908 0.0609
-0.750 0.4337 0.01703 0.00767 -0.1109 0.8860 0.0691
-0.500 0.4615 0.01656 0.00721 -0.1108 0.8765 0.0754
-0.250 0.4935 0.01605 0.00660 -0.1112 0.8692 0.0798
0.000 0.5260 0.01563 0.00612 -0.1118 0.8607 0.0880
0.250 0.5565 0.01526 0.00576 -0.1120 0.8505 0.1141
0.500 0.5884 0.01481 0.00551 -0.1126 0.8401 0.1937
1.000 0.6579 0.01302 0.00506 -0.1149 0.8176 1.0000
1.250 0.6876 0.01301 0.00492 -0.1150 0.8038 1.0000
1.500 0.7170 0.01302 0.00483 -0.1149 0.7896 1.0000
1.750 0.7461 0.01306 0.00478 -0.1149 0.7750 1.0000
2.000 0.7743 0.01312 0.00479 -0.1147 0.7594 1.0000
2.250 0.8016 0.01322 0.00487 -0.1143 0.7427 1.0000
2.500 0.8287 0.01335 0.00496 -0.1140 0.7256 1.0000
2.750 0.8556 0.01349 0.00508 -0.1135 0.7081 1.0000
3.000 0.8822 0.01365 0.00526 -0.1131 0.6904 1.0000
3.250 0.9078 0.01384 0.00546 -0.1124 0.6711 1.0000
3.500 0.9321 0.01403 0.00560 -0.1114 0.6441 1.0000
3.750 0.9550 0.01425 0.00574 -0.1101 0.6101 1.0000
4.000 0.9772 0.01457 0.00591 -0.1086 0.5716 1.0000
4.250 0.9996 0.01496 0.00619 -0.1074 0.5406 1.0000
4.500 1.0222 0.01537 0.00656 -0.1062 0.5152 1.0000
4.750 1.0443 0.01580 0.00698 -0.1051 0.4887 1.0000
5.000 1.0657 0.01623 0.00749 -0.1038 0.4584 1.0000
5.250 1.0853 0.01671 0.00796 -0.1022 0.4145 1.0000
5.500 1.1028 0.01737 0.00846 -0.1002 0.3555 1.0000
5.750 1.1164 0.01849 0.00917 -0.0979 0.2643 1.0000
6.000 1.1224 0.02075 0.01049 -0.0949 0.1132 1.0000
6.250 1.1338 0.02252 0.01191 -0.0925 0.0643 1.0000
6.500 1.1489 0.02378 0.01323 -0.0905 0.0487 1.0000
6.750 1.1611 0.02528 0.01480 -0.0881 0.0401 1.0000
7.000 1.1698 0.02701 0.01667 -0.0853 0.0342 1.0000
7.250 1.1795 0.02863 0.01850 -0.0824 0.0295 1.0000
7.500 1.1878 0.03046 0.02040 -0.0796 0.0258 1.0000
7.750 1.1979 0.03290 0.02285 -0.0771 0.0237 1.0000
8.000 1.2164 0.03444 0.02467 -0.0755 0.0209 1.0000
8.250 1.2367 0.03666 0.02712 -0.0743 0.0186 1.0000
8.500 1.2589 0.03942 0.03013 -0.0733 0.0172 1.0000
8.750 1.2776 0.04222 0.03331 -0.0720 0.0161 1.0000
9.000 1.2894 0.04485 0.03617 -0.0704 0.0147 1.0000
9.250 1.2983 0.04939 0.04100 -0.0688 0.0136 1.0000
9.500 1.3019 0.05274 0.04476 -0.0660 0.0132 1.0000
9.750 1.3020 0.05597 0.04840 -0.0630 0.0130 1.0000
10.000 1.2966 0.05914 0.05193 -0.0595 0.0129 1.0000
10.250 1.2873 0.06240 0.05551 -0.0560 0.0128 1.0000
10.500 1.2757 0.06581 0.05922 -0.0531 0.0128 1.0000
10.750 1.2620 0.06947 0.06317 -0.0507 0.0128 1.0000
11.000 1.2466 0.07348 0.06744 -0.0491 0.0128 1.0000
11.250 1.2301 0.07787 0.07208 -0.0484 0.0128 1.0000
11.500 1.2133 0.08266 0.07710 -0.0486 0.0128 1.0000
11.750 1.1957 0.08796 0.08260 -0.0497 0.0129 1.0000
12.000 1.1779 0.09375 0.08859 -0.0518 0.0129 1.0000
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Polar data table (+)
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