GOE 375 AIRFOIL (goe375-il) Xfoil prediction polar at RE=500,000 Ncrit=5
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Airfoil: GOE 375 AIRFOIL (goe375-il) Reynolds number: 500,000 Max Cl/Cd: 91.48 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe375-il-500000-n5.txt Download as CSV file: xf-goe375-il-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 375 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-7.750 -0.3178 0.09099 0.08888 -0.0152 1.0000 0.0076
-7.500 -0.3162 0.08856 0.08649 -0.0153 1.0000 0.0082
-7.250 -0.3173 0.08634 0.08431 -0.0149 1.0000 0.0083
-7.000 -0.3160 0.08385 0.08186 -0.0153 1.0000 0.0084
-6.750 -0.2987 0.08014 0.07816 -0.0208 0.9960 0.0091
-6.500 -0.2737 0.07581 0.07382 -0.0276 0.9839 0.0091
-6.250 -0.2389 0.07094 0.06890 -0.0374 0.9695 0.0092
-6.000 -0.2028 0.06591 0.06381 -0.0460 0.9547 0.0092
-5.750 -0.1649 0.06097 0.05878 -0.0541 0.9377 0.0092
-5.500 -0.1287 0.05625 0.05394 -0.0611 0.9150 0.0092
-5.250 -0.0998 0.05231 0.04984 -0.0654 0.8882 0.0092
-4.750 -0.0617 0.04621 0.04346 -0.0684 0.8483 0.0085
-4.500 -0.0380 0.04293 0.04002 -0.0702 0.8340 0.0081
-4.250 -0.0137 0.03978 0.03668 -0.0715 0.8183 0.0080
-4.000 0.0114 0.03675 0.03345 -0.0725 0.8039 0.0082
-3.750 0.0376 0.03367 0.03013 -0.0730 0.7888 0.0087
-3.500 0.0659 0.03008 0.02624 -0.0731 0.7744 0.0092
-3.250 0.0911 0.02733 0.02323 -0.0730 0.7592 0.0092
-3.000 0.1154 0.02549 0.02120 -0.0728 0.7428 0.0095
-2.750 0.1404 0.02396 0.01948 -0.0724 0.7253 0.0100
-2.500 0.1661 0.02219 0.01745 -0.0718 0.7057 0.0105
-2.250 0.1932 0.01981 0.01466 -0.0706 0.6840 0.0122
-2.000 0.2182 0.01833 0.01286 -0.0697 0.6543 0.0129
-1.750 0.2422 0.01770 0.01195 -0.0690 0.6150 0.0136
-1.500 0.2670 0.01679 0.01070 -0.0680 0.5754 0.0147
-1.250 0.2933 0.01546 0.00890 -0.0667 0.5445 0.0170
-1.000 0.3182 0.01506 0.00833 -0.0663 0.5186 0.0176
-0.750 0.3439 0.01454 0.00761 -0.0658 0.4974 0.0189
-0.500 0.3709 0.01416 0.00692 -0.0649 0.4787 0.0212
-0.250 0.3968 0.01348 0.00603 -0.0644 0.4599 0.0223
0.000 0.4224 0.01304 0.00549 -0.0640 0.4416 0.0231
0.250 0.4484 0.01281 0.00515 -0.0636 0.4242 0.0251
0.500 0.4747 0.01246 0.00465 -0.0631 0.4093 0.0258
0.750 0.5009 0.01221 0.00426 -0.0626 0.3927 0.0264
1.000 0.5267 0.01209 0.00399 -0.0621 0.3710 0.0270
1.500 0.5772 0.01171 0.00338 -0.0611 0.3233 0.0293
1.750 0.6029 0.01169 0.00324 -0.0606 0.3054 0.0286
2.000 0.6285 0.01161 0.00310 -0.0601 0.2906 0.0284
2.250 0.6538 0.01150 0.00294 -0.0596 0.2775 0.0285
2.500 0.6790 0.01139 0.00280 -0.0591 0.2661 0.0291
2.750 0.7044 0.01138 0.00275 -0.0587 0.2557 0.0299
3.000 0.7302 0.01138 0.00275 -0.0583 0.2469 0.0307
3.250 0.7559 0.01144 0.00277 -0.0579 0.2388 0.0316
3.500 0.7817 0.01152 0.00284 -0.0575 0.2308 0.0334
3.750 0.8074 0.01162 0.00291 -0.0571 0.2235 0.0337
4.000 0.8332 0.01171 0.00299 -0.0567 0.2166 0.0336
4.250 0.8587 0.01185 0.00309 -0.0563 0.2107 0.0335
4.500 0.8847 0.01195 0.00319 -0.0560 0.2057 0.0335
4.750 0.9103 0.01210 0.00333 -0.0556 0.2000 0.0338
5.000 0.9359 0.01227 0.00348 -0.0552 0.1950 0.0342
5.250 0.9616 0.01241 0.00363 -0.0549 0.1898 0.0353
5.500 0.9869 0.01259 0.00382 -0.0545 0.1841 0.0380
5.750 1.0124 0.01277 0.00402 -0.0541 0.1792 0.0440
6.000 1.0509 0.01155 0.00447 -0.0572 0.1724 1.0000
6.250 1.0755 0.01181 0.00472 -0.0567 0.1670 1.0000
6.500 1.1005 0.01203 0.00497 -0.0562 0.1619 1.0000
6.750 1.1248 0.01231 0.00524 -0.0557 0.1559 1.0000
7.000 1.1491 0.01260 0.00551 -0.0552 0.1468 1.0000
7.250 1.1727 0.01295 0.00583 -0.0546 0.1366 1.0000
7.750 1.2195 0.01367 0.00652 -0.0534 0.1186 1.0000
8.000 1.2424 0.01408 0.00691 -0.0527 0.1096 1.0000
8.250 1.2645 0.01457 0.00736 -0.0520 0.0963 1.0000
8.750 1.2922 0.01743 0.00971 -0.0484 0.0119 1.0000
9.000 1.3132 0.01799 0.01037 -0.0474 0.0097 1.0000
9.250 1.3329 0.01867 0.01114 -0.0464 0.0081 1.0000
9.500 1.3511 0.01949 0.01210 -0.0451 0.0069 1.0000
9.750 1.3701 0.02017 0.01290 -0.0439 0.0064 1.0000
10.000 1.3877 0.02095 0.01380 -0.0426 0.0058 1.0000
10.250 1.4040 0.02180 0.01475 -0.0412 0.0053 1.0000
10.500 1.4160 0.02298 0.01605 -0.0392 0.0047 1.0000
10.750 1.4298 0.02390 0.01709 -0.0375 0.0045 1.0000
11.000 1.4417 0.02487 0.01817 -0.0355 0.0042 1.0000
11.250 1.4482 0.02596 0.01941 -0.0328 0.0040 1.0000
11.500 1.4526 0.02713 0.02070 -0.0299 0.0038 1.0000
11.750 1.4561 0.02842 0.02210 -0.0273 0.0036 1.0000
12.000 1.4564 0.03000 0.02381 -0.0247 0.0035 1.0000
12.250 1.4545 0.03190 0.02585 -0.0225 0.0034 1.0000
12.500 1.4512 0.03413 0.02820 -0.0209 0.0033 1.0000
12.750 1.4455 0.03687 0.03108 -0.0198 0.0033 1.0000
13.000 1.4360 0.04033 0.03469 -0.0195 0.0031 1.0000
13.250 1.4228 0.04470 0.03922 -0.0200 0.0031 1.0000
13.500 1.4087 0.04980 0.04449 -0.0216 0.0030 1.0000
13.750 1.3950 0.05545 0.05030 -0.0240 0.0030 1.0000
14.000 1.3813 0.06149 0.05649 -0.0268 0.0030 1.0000
14.250 1.3652 0.06806 0.06322 -0.0298 0.0030 1.0000
14.500 1.3478 0.07489 0.07019 -0.0329 0.0030 1.0000
14.750 1.3282 0.08213 0.07756 -0.0361 0.0030 1.0000
15.000 1.3112 0.08903 0.08458 -0.0392 0.0030 1.0000
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Polar data table (+)
Polar graphs
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