GOE 184 (MVA H.29) AIRFOIL (goe184-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 184 (MVA H.29) AIRFOIL (goe184-il) Reynolds number: 200,000 Max Cl/Cd: 79.41 at α=7.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe184-il-200000.txt Download as CSV file: xf-goe184-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 184 (MVA H.29) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.000 -0.3097 0.09511 0.09174 -0.0257 1.0000 0.0478
-7.750 -0.3213 0.09393 0.09069 -0.0316 1.0000 0.0485
-7.500 -0.3153 0.08963 0.08642 -0.0289 1.0000 0.0493
-7.250 -0.3057 0.08700 0.08381 -0.0259 1.0000 0.0507
-7.000 -0.3051 0.08500 0.08188 -0.0251 1.0000 0.0521
-6.750 -0.3104 0.08336 0.08031 -0.0239 1.0000 0.0533
-6.500 -0.3231 0.08231 0.07935 -0.0217 1.0000 0.0544
-6.250 -0.2773 0.07516 0.07211 -0.0439 0.9913 0.0582
-6.000 -0.2577 0.07169 0.06865 -0.0424 0.9873 0.0595
-5.750 -0.2245 0.06790 0.06483 -0.0475 0.9831 0.0625
-5.500 -0.1625 0.06041 0.05708 -0.0689 0.9732 0.0689
-5.250 -0.1355 0.05675 0.05343 -0.0704 0.9701 0.0702
-5.000 -0.1043 0.05339 0.05003 -0.0740 0.9622 0.0723
-4.750 -0.0329 0.04787 0.04393 -0.0909 0.9560 0.0801
-4.500 -0.0089 0.04264 0.03873 -0.0933 0.9462 0.0814
-4.250 0.0221 0.03958 0.03562 -0.0956 0.9384 0.0827
-4.000 0.0710 0.01415 0.00963 -0.0982 0.8978 0.0690
-3.750 0.0935 0.01253 0.00793 -0.0980 0.8840 0.0702
-3.500 0.1308 0.01953 0.01328 -0.1063 0.9044 0.0584
-3.250 0.1585 0.01791 0.01136 -0.1059 0.8904 0.0592
-3.000 0.1854 0.01694 0.01020 -0.1053 0.8756 0.0606
-2.750 0.2120 0.01630 0.00938 -0.1045 0.8608 0.0635
-2.500 0.2394 0.01537 0.00813 -0.1038 0.8467 0.0660
-2.250 0.2666 0.01456 0.00705 -0.1031 0.8324 0.0686
-2.000 0.2931 0.01396 0.00642 -0.1024 0.8176 0.0728
-1.750 0.3202 0.01358 0.00583 -0.1017 0.8028 0.0800
-1.500 0.3469 0.01303 0.00524 -0.1012 0.7875 0.0947
-1.250 0.3737 0.01285 0.00499 -0.1007 0.7716 0.1096
-1.000 0.4005 0.01283 0.00488 -0.1002 0.7552 0.1194
-0.750 0.4272 0.01274 0.00472 -0.0997 0.7388 0.1269
-0.500 0.4542 0.01269 0.00458 -0.0993 0.7226 0.1318
-0.250 0.4813 0.01269 0.00445 -0.0988 0.7069 0.1363
0.000 0.5082 0.01259 0.00435 -0.0985 0.6917 0.1436
0.250 0.5353 0.01258 0.00427 -0.0982 0.6770 0.1498
0.500 0.5625 0.01249 0.00414 -0.0979 0.6627 0.1549
0.750 0.5897 0.01243 0.00406 -0.0976 0.6487 0.1625
1.000 0.6169 0.01236 0.00397 -0.0973 0.6343 0.1695
1.250 0.6441 0.01228 0.00390 -0.0970 0.6196 0.1799
1.500 0.6712 0.01216 0.00385 -0.0968 0.6052 0.2069
1.750 0.6929 0.01049 0.00386 -0.0953 0.5921 1.0000
2.000 0.7201 0.01068 0.00387 -0.0949 0.5787 1.0000
2.250 0.7471 0.01090 0.00395 -0.0946 0.5661 1.0000
2.500 0.7740 0.01115 0.00405 -0.0943 0.5537 1.0000
2.750 0.8008 0.01142 0.00417 -0.0940 0.5413 1.0000
3.000 0.8276 0.01169 0.00434 -0.0937 0.5290 1.0000
3.250 0.8544 0.01194 0.00455 -0.0934 0.5171 1.0000
3.500 0.8812 0.01223 0.00476 -0.0932 0.5062 1.0000
3.750 0.9079 0.01254 0.00497 -0.0929 0.4959 1.0000
4.000 0.9345 0.01277 0.00521 -0.0927 0.4848 1.0000
4.250 0.9612 0.01303 0.00546 -0.0924 0.4747 1.0000
4.500 0.9877 0.01331 0.00566 -0.0921 0.4655 1.0000
4.750 1.0141 0.01350 0.00591 -0.0918 0.4548 1.0000
5.000 1.0404 0.01374 0.00615 -0.0915 0.4454 1.0000
5.250 1.0666 0.01398 0.00636 -0.0912 0.4365 1.0000
5.500 1.0929 0.01420 0.00666 -0.0909 0.4275 1.0000
5.750 1.1190 0.01448 0.00692 -0.0906 0.4200 1.0000
6.000 1.1449 0.01469 0.00722 -0.0903 0.4103 1.0000
6.250 1.1703 0.01491 0.00747 -0.0899 0.3995 1.0000
6.500 1.1953 0.01514 0.00773 -0.0894 0.3880 1.0000
6.750 1.2199 0.01541 0.00800 -0.0888 0.3763 1.0000
7.000 1.2442 0.01567 0.00831 -0.0883 0.3627 1.0000
7.250 1.2681 0.01597 0.00865 -0.0877 0.3481 1.0000
7.500 1.2911 0.01633 0.00902 -0.0869 0.3317 1.0000
7.750 1.3141 0.01669 0.00943 -0.0862 0.3145 1.0000
8.000 1.3368 0.01706 0.00987 -0.0855 0.2942 1.0000
8.250 1.3584 0.01750 0.01032 -0.0846 0.2689 1.0000
8.500 1.3783 0.01809 0.01085 -0.0836 0.2269 1.0000
8.750 1.3899 0.01950 0.01183 -0.0817 0.1737 1.0000
9.000 1.4026 0.02089 0.01305 -0.0798 0.1362 1.0000
9.250 1.4085 0.02285 0.01455 -0.0773 0.0760 1.0000
9.500 1.4148 0.02463 0.01613 -0.0746 0.0498 1.0000
9.750 1.4224 0.02614 0.01763 -0.0721 0.0432 1.0000
10.000 1.4239 0.02780 0.01938 -0.0688 0.0396 1.0000
10.250 1.4277 0.02934 0.02107 -0.0660 0.0379 1.0000
10.500 1.4291 0.03114 0.02301 -0.0634 0.0365 1.0000
10.750 1.4286 0.03324 0.02524 -0.0611 0.0352 1.0000
11.000 1.4261 0.03568 0.02780 -0.0592 0.0341 1.0000
11.250 1.4214 0.03854 0.03074 -0.0575 0.0330 1.0000
11.500 1.4146 0.04178 0.03405 -0.0560 0.0320 1.0000
11.750 1.4123 0.04469 0.03705 -0.0546 0.0311 1.0000
12.000 1.4157 0.04709 0.03957 -0.0536 0.0304 1.0000
12.250 1.4189 0.04953 0.04214 -0.0525 0.0297 1.0000
12.500 1.4228 0.05193 0.04463 -0.0513 0.0291 1.0000
12.750 1.4279 0.05424 0.04704 -0.0500 0.0285 1.0000
13.000 1.4342 0.05649 0.04938 -0.0487 0.0279 1.0000
13.250 1.4401 0.05884 0.05182 -0.0475 0.0272 1.0000
13.500 1.4456 0.06128 0.05434 -0.0464 0.0264 1.0000
13.750 1.4545 0.06358 0.05666 -0.0449 0.0254 1.0000
14.000 1.4731 0.06657 0.05977 -0.0421 0.0245 1.0000
14.250 1.4728 0.07039 0.06380 -0.0413 0.0243 1.0000
14.500 1.4657 0.07415 0.06780 -0.0412 0.0243 1.0000
14.750 1.4581 0.07823 0.07211 -0.0413 0.0242 1.0000
15.000 1.4487 0.08265 0.07676 -0.0417 0.0242 1.0000
15.250 1.4379 0.08743 0.08176 -0.0424 0.0242 1.0000
15.500 1.4261 0.09259 0.08714 -0.0435 0.0243 1.0000
15.750 1.4163 0.09815 0.09293 -0.0442 0.0244 1.0000
16.000 1.4028 0.10324 0.09822 -0.0463 0.0245 1.0000
16.250 1.3890 0.10864 0.10380 -0.0490 0.0246 1.0000
16.500 1.3749 0.11437 0.10972 -0.0522 0.0247 1.0000
16.750 1.3592 0.12074 0.11630 -0.0562 0.0248 1.0000
17.000 1.3419 0.12792 0.12370 -0.0611 0.0250 1.0000
17.250 1.3200 0.13680 0.13283 -0.0675 0.0254 1.0000
17.500 1.2809 0.15111 0.14751 -0.0785 0.0262 1.0000
17.750 1.1558 0.20173 0.19852 -0.1124 0.0332 1.0000
18.000 1.1674 0.20155 0.19839 -0.1122 0.0325 1.0000
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