GOE 309 (MVA H.41) AIRFOIL (goe309-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: GOE 309 (MVA H.41) AIRFOIL (goe309-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.8 at α=4.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe309-il-1000000.txt Download as CSV file: xf-goe309-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 309 (MVA H.41) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 1.000 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3637 0.08521 0.08381 -0.0199 0.9923 0.0118
-7.500 -0.3521 0.08092 0.07950 -0.0255 0.9679 0.0128
-7.000 -0.4213 0.01822 0.01477 -0.0520 0.9141 0.0111
-6.750 -0.3955 0.01839 0.01492 -0.0514 0.8943 0.0116
-6.500 -0.3718 0.01754 0.01386 -0.0507 0.8710 0.0121
-6.250 -0.2907 0.05889 0.05688 -0.0423 0.8375 0.0139
-6.000 -0.2790 0.05385 0.05167 -0.0445 0.8183 0.0133
-5.750 -0.2992 0.01349 0.00875 -0.0490 0.8132 0.0145
-5.500 -0.2717 0.01347 0.00869 -0.0489 0.7986 0.0153
-5.250 -0.2436 0.01367 0.00887 -0.0489 0.7859 0.0160
-5.000 -0.2156 0.01373 0.00887 -0.0489 0.7744 0.0170
-4.750 -0.1877 0.01366 0.00871 -0.0488 0.7638 0.0181
-4.500 -0.1596 0.01375 0.00870 -0.0488 0.7537 0.0187
-4.250 -0.1338 0.01228 0.00700 -0.0485 0.7447 0.0204
-4.000 -0.1058 0.01228 0.00697 -0.0486 0.7361 0.0214
-3.750 -0.0778 0.01219 0.00681 -0.0486 0.7272 0.0227
-3.500 -0.0496 0.01207 0.00662 -0.0486 0.7186 0.0241
-3.250 -0.0215 0.01202 0.00648 -0.0486 0.7102 0.0250
-3.000 0.0058 0.01100 0.00526 -0.0484 0.7022 0.0262
-2.750 0.0329 0.01029 0.00447 -0.0483 0.6944 0.0281
-2.500 0.0610 0.01003 0.00416 -0.0483 0.6857 0.0295
-2.250 0.0889 0.00974 0.00380 -0.0483 0.6771 0.0307
-2.000 0.1168 0.00949 0.00348 -0.0482 0.6681 0.0319
-1.750 0.1448 0.00924 0.00318 -0.0482 0.6593 0.0329
-1.500 0.1726 0.00898 0.00285 -0.0482 0.6501 0.0334
-1.250 0.2005 0.00877 0.00257 -0.0481 0.6398 0.0339
-1.000 0.2285 0.00859 0.00234 -0.0481 0.6281 0.0344
-0.750 0.2561 0.00836 0.00202 -0.0480 0.6148 0.0354
-0.500 0.2837 0.00813 0.00170 -0.0479 0.6002 0.0380
-0.250 0.3116 0.00804 0.00155 -0.0479 0.5849 0.0403
0.000 0.3396 0.00800 0.00145 -0.0479 0.5701 0.0423
0.250 0.3675 0.00798 0.00136 -0.0479 0.5546 0.0447
0.750 0.4231 0.00795 0.00135 -0.0480 0.5206 0.0988
1.000 0.4511 0.00799 0.00136 -0.0481 0.5046 0.1107
1.250 0.4790 0.00803 0.00137 -0.0482 0.4914 0.1206
1.500 0.5070 0.00807 0.00138 -0.0483 0.4798 0.1293
1.750 0.5350 0.00807 0.00140 -0.0484 0.4696 0.1449
2.000 0.5624 0.00792 0.00150 -0.0486 0.4603 0.2658
2.250 0.5779 0.00637 0.00161 -0.0464 0.4522 0.9000
2.500 0.6005 0.00637 0.00170 -0.0449 0.4443 0.9583
2.750 0.6360 0.00650 0.00179 -0.0465 0.4354 0.9861
3.000 0.6775 0.00664 0.00190 -0.0496 0.4263 0.9942
3.250 0.7193 0.00677 0.00199 -0.0529 0.4176 0.9969
3.500 0.7568 0.00693 0.00208 -0.0552 0.4076 0.9991
4.000 0.8122 0.00718 0.00224 -0.0555 0.3820 1.0000
4.250 0.8364 0.00735 0.00233 -0.0549 0.3645 1.0000
4.500 0.8601 0.00758 0.00244 -0.0543 0.3368 1.0000
4.750 0.8834 0.00789 0.00260 -0.0536 0.3043 1.0000
5.000 0.9053 0.00836 0.00284 -0.0527 0.2593 1.0000
5.250 0.9260 0.00900 0.00319 -0.0518 0.2090 1.0000
5.500 0.9474 0.00957 0.00353 -0.0509 0.1704 1.0000
5.750 0.9681 0.01022 0.00391 -0.0499 0.1261 1.0000
6.000 0.9814 0.01182 0.00498 -0.0479 0.0188 1.0000
6.250 1.0055 0.01215 0.00533 -0.0474 0.0153 1.0000
6.500 1.0298 0.01247 0.00570 -0.0469 0.0139 1.0000
6.750 1.0539 0.01283 0.00612 -0.0464 0.0130 1.0000
7.000 1.0775 0.01325 0.00658 -0.0458 0.0121 1.0000
7.250 1.1004 0.01373 0.00711 -0.0452 0.0113 1.0000
7.500 1.1220 0.01437 0.00782 -0.0443 0.0105 1.0000
7.750 1.1400 0.01538 0.00896 -0.0430 0.0096 1.0000
8.000 1.1631 0.01578 0.00940 -0.0424 0.0092 1.0000
8.250 1.1840 0.01640 0.01007 -0.0415 0.0088 1.0000
8.500 1.2035 0.01711 0.01084 -0.0405 0.0084 1.0000
8.750 1.2219 0.01788 0.01167 -0.0393 0.0081 1.0000
9.000 1.2391 0.01868 0.01254 -0.0380 0.0078 1.0000
9.250 1.2550 0.01954 0.01346 -0.0365 0.0075 1.0000
9.500 1.2686 0.02050 0.01447 -0.0348 0.0072 1.0000
9.750 1.2766 0.02169 0.01572 -0.0322 0.0069 1.0000
10.000 1.2741 0.02333 0.01743 -0.0283 0.0067 1.0000
10.250 1.2672 0.02564 0.01981 -0.0244 0.0066 1.0000
10.500 1.2699 0.02751 0.02176 -0.0220 0.0064 1.0000
10.750 1.2840 0.02835 0.02269 -0.0211 0.0062 1.0000
11.000 1.2939 0.02966 0.02408 -0.0200 0.0060 1.0000
11.250 1.3003 0.03141 0.02591 -0.0186 0.0059 1.0000
11.500 1.3064 0.03329 0.02787 -0.0172 0.0058 1.0000
11.750 1.3130 0.03519 0.02986 -0.0159 0.0057 1.0000
12.000 1.3200 0.03713 0.03187 -0.0147 0.0056 1.0000
12.250 1.3273 0.03911 0.03393 -0.0134 0.0056 1.0000
12.500 1.3345 0.04116 0.03608 -0.0122 0.0055 1.0000
12.750 1.3407 0.04334 0.03836 -0.0110 0.0054 1.0000
13.000 1.3455 0.04566 0.04079 -0.0101 0.0053 1.0000
13.250 1.3490 0.04820 0.04346 -0.0092 0.0053 1.0000
13.500 1.3503 0.05100 0.04640 -0.0083 0.0052 1.0000
13.750 1.3494 0.05412 0.04966 -0.0077 0.0052 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 309 (MVA H.41) AIRFOIL (goe309-il)