GOE 122 (MVA H.2) AIRFOIL (goe122-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 122 (MVA H.2) AIRFOIL (goe122-il) Reynolds number: 200,000 Max Cl/Cd: 72.33 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe122-il-200000-n5.txt Download as CSV file: xf-goe122-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 122 (MVA H.2) AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3928 0.09531 0.09198 -0.0079 1.0000 0.0201
-7.750 -0.3869 0.09208 0.08879 -0.0098 1.0000 0.0204
-7.500 -0.3814 0.08885 0.08560 -0.0118 1.0000 0.0208
-7.250 -0.3742 0.08546 0.08224 -0.0146 1.0000 0.0211
-7.000 -0.3640 0.08178 0.07860 -0.0182 1.0000 0.0215
-6.750 -0.3481 0.07774 0.07456 -0.0253 1.0000 0.0236
-6.500 -0.3290 0.07321 0.07000 -0.0328 1.0000 0.0240
-6.250 -0.3125 0.06895 0.06571 -0.0374 1.0000 0.0241
-5.750 -0.2690 0.05970 0.05638 -0.0452 0.9807 0.0235
-5.500 -0.2413 0.05463 0.05122 -0.0504 0.9670 0.0211
-5.250 -0.2055 0.04870 0.04509 -0.0575 0.9532 0.0204
-5.000 -0.1706 0.04409 0.04025 -0.0625 0.9392 0.0224
-4.750 -0.1366 0.03875 0.03457 -0.0667 0.9253 0.0231
-4.500 -0.1058 0.03381 0.02923 -0.0690 0.9118 0.0234
-4.250 -0.0778 0.02981 0.02478 -0.0702 0.8992 0.0253
-4.000 -0.0540 0.02888 0.02377 -0.0704 0.8864 0.0275
-3.750 -0.0265 0.02589 0.02036 -0.0706 0.8745 0.0283
-3.500 0.0009 0.02330 0.01730 -0.0704 0.8625 0.0293
-3.250 0.0292 0.02184 0.01531 -0.0699 0.8496 0.0319
-3.000 0.0561 0.01986 0.01290 -0.0696 0.8363 0.0325
-2.750 0.0824 0.01810 0.01084 -0.0693 0.8222 0.0335
-2.500 0.1085 0.01727 0.00990 -0.0691 0.8071 0.0356
-2.250 0.1355 0.01633 0.00872 -0.0686 0.7914 0.0366
-2.000 0.1626 0.01546 0.00759 -0.0681 0.7748 0.0371
-1.750 0.1897 0.01473 0.00666 -0.0676 0.7570 0.0377
-1.500 0.2166 0.01416 0.00591 -0.0671 0.7390 0.0385
-1.250 0.2436 0.01375 0.00534 -0.0667 0.7210 0.0403
-1.000 0.2704 0.01331 0.00476 -0.0662 0.7030 0.0408
-0.750 0.2972 0.01291 0.00425 -0.0658 0.6850 0.0410
-0.500 0.3241 0.01258 0.00383 -0.0655 0.6671 0.0413
-0.250 0.3511 0.01233 0.00349 -0.0652 0.6502 0.0418
0.000 0.3783 0.01215 0.00321 -0.0649 0.6335 0.0423
0.250 0.4053 0.01198 0.00293 -0.0647 0.6153 0.0435
0.500 0.4324 0.01190 0.00273 -0.0644 0.5963 0.0451
0.750 0.4597 0.01186 0.00262 -0.0642 0.5761 0.0486
1.000 0.4868 0.01188 0.00253 -0.0640 0.5553 0.0524
1.250 0.5140 0.01191 0.00247 -0.0638 0.5354 0.0565
1.500 0.5412 0.01188 0.00247 -0.0637 0.5152 0.0879
1.750 0.5668 0.00992 0.00256 -0.0634 0.4968 1.0000
2.000 0.5936 0.01013 0.00259 -0.0631 0.4795 1.0000
2.250 0.6205 0.01034 0.00265 -0.0629 0.4648 1.0000
2.500 0.6474 0.01054 0.00274 -0.0627 0.4518 1.0000
2.750 0.6744 0.01075 0.00287 -0.0626 0.4403 1.0000
3.000 0.7012 0.01097 0.00301 -0.0624 0.4302 1.0000
3.250 0.7281 0.01119 0.00317 -0.0622 0.4208 1.0000
3.500 0.7551 0.01140 0.00336 -0.0621 0.4123 1.0000
3.750 0.7817 0.01165 0.00354 -0.0619 0.4034 1.0000
4.000 0.8085 0.01186 0.00375 -0.0618 0.3924 1.0000
4.250 0.8349 0.01211 0.00396 -0.0616 0.3767 1.0000
4.500 0.8609 0.01238 0.00416 -0.0613 0.3579 1.0000
4.750 0.8872 0.01262 0.00437 -0.0611 0.3400 1.0000
5.000 0.9135 0.01287 0.00464 -0.0610 0.3269 1.0000
5.250 0.9397 0.01313 0.00490 -0.0608 0.3132 1.0000
5.500 0.9658 0.01340 0.00519 -0.0606 0.2973 1.0000
5.750 0.9916 0.01371 0.00550 -0.0603 0.2781 1.0000
6.000 1.0163 0.01415 0.00586 -0.0600 0.2452 1.0000
6.250 1.0399 0.01475 0.00630 -0.0596 0.2070 1.0000
6.500 1.0632 0.01541 0.00684 -0.0592 0.1811 1.0000
6.750 1.0865 0.01605 0.00746 -0.0587 0.1623 1.0000
7.000 1.1093 0.01677 0.00811 -0.0582 0.1338 1.0000
7.500 1.1468 0.01927 0.01013 -0.0565 0.0483 1.0000
7.750 1.1681 0.02011 0.01105 -0.0557 0.0433 1.0000
8.000 1.1896 0.02086 0.01198 -0.0550 0.0400 1.0000
8.250 1.2092 0.02182 0.01306 -0.0541 0.0364 1.0000
8.500 1.2255 0.02310 0.01448 -0.0529 0.0328 1.0000
8.750 1.2451 0.02392 0.01546 -0.0520 0.0304 1.0000
9.000 1.2622 0.02494 0.01662 -0.0509 0.0274 1.0000
9.250 1.2758 0.02625 0.01804 -0.0495 0.0247 1.0000
9.500 1.2846 0.02792 0.01981 -0.0475 0.0228 1.0000
9.750 1.2985 0.02902 0.02108 -0.0460 0.0210 1.0000
10.000 1.3100 0.03023 0.02242 -0.0444 0.0190 1.0000
10.250 1.3191 0.03140 0.02367 -0.0425 0.0175 1.0000
10.500 1.3243 0.03294 0.02529 -0.0405 0.0165 1.0000
10.750 1.3237 0.03515 0.02759 -0.0384 0.0157 1.0000
11.000 1.3278 0.03713 0.02973 -0.0369 0.0151 1.0000
11.250 1.3313 0.03926 0.03205 -0.0355 0.0144 1.0000
11.500 1.3351 0.04145 0.03438 -0.0345 0.0136 1.0000
11.750 1.3389 0.04367 0.03673 -0.0339 0.0129 1.0000
12.000 1.3422 0.04603 0.03920 -0.0336 0.0123 1.0000
12.250 1.3440 0.04864 0.04192 -0.0336 0.0118 1.0000
12.500 1.3429 0.05173 0.04512 -0.0337 0.0114 1.0000
12.750 1.3387 0.05529 0.04879 -0.0334 0.0110 1.0000
13.000 1.3371 0.05869 0.05239 -0.0333 0.0108 1.0000
13.250 1.3340 0.06234 0.05625 -0.0335 0.0106 1.0000
13.500 1.3295 0.06628 0.06039 -0.0338 0.0103 1.0000
13.750 1.3234 0.07054 0.06486 -0.0345 0.0101 1.0000
14.000 1.3156 0.07514 0.06967 -0.0355 0.0100 1.0000
14.250 1.3064 0.08010 0.07483 -0.0368 0.0098 1.0000
14.500 1.2957 0.08545 0.08038 -0.0386 0.0097 1.0000
14.750 1.2840 0.09119 0.08633 -0.0409 0.0096 1.0000
15.000 1.2714 0.09736 0.09271 -0.0436 0.0095 1.0000
15.250 1.2576 0.10395 0.09950 -0.0467 0.0094 1.0000
15.500 1.2430 0.11097 0.10671 -0.0503 0.0094 1.0000
15.750 1.2275 0.11850 0.11440 -0.0543 0.0093 1.0000
16.000 1.2103 0.12675 0.12284 -0.0589 0.0094 1.0000
16.250 1.1916 0.13579 0.13205 -0.0642 0.0094 1.0000
16.500 1.1713 0.14587 0.14230 -0.0703 0.0096 1.0000
16.750 1.1493 0.15728 0.15387 -0.0773 0.0098 1.0000
17.000 1.1247 0.17070 0.16741 -0.0854 0.0100 1.0000
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Polar data table (+)
Polar graphs
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