GOE 741 AIRFOIL (goe741-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 741 AIRFOIL (goe741-il) Reynolds number: 1,000,000 Max Cl/Cd: 106.26 at α=7.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe741-il-1000000-n5.txt Download as CSV file: xf-goe741-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 741 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-15.500 -1.1188 0.04174 0.03783 -0.0558 0.6795 0.0218
-15.250 -1.1436 0.03772 0.03362 -0.0549 0.6735 0.0218
-15.000 -1.1512 0.03556 0.03133 -0.0529 0.6671 0.0219
-14.750 -1.1593 0.03357 0.02920 -0.0500 0.6609 0.0219
-14.500 -1.1606 0.03212 0.02762 -0.0470 0.6533 0.0219
-14.250 -1.1602 0.03084 0.02622 -0.0438 0.6465 0.0220
-14.000 -1.1556 0.02981 0.02509 -0.0408 0.6389 0.0221
-13.750 -1.1454 0.02878 0.02394 -0.0387 0.6303 0.0222
-13.500 -1.1336 0.02774 0.02278 -0.0367 0.6223 0.0223
-13.250 -1.1194 0.02683 0.02175 -0.0349 0.6123 0.0224
-13.000 -1.1031 0.02601 0.02083 -0.0333 0.6040 0.0225
-12.750 -1.0862 0.02520 0.01991 -0.0318 0.5953 0.0226
-12.500 -1.0681 0.02444 0.01904 -0.0304 0.5879 0.0228
-12.250 -1.0494 0.02369 0.01819 -0.0290 0.5803 0.0229
-12.000 -1.0303 0.02295 0.01733 -0.0277 0.5729 0.0230
-11.750 -1.0104 0.02223 0.01652 -0.0264 0.5667 0.0231
-11.500 -0.9897 0.02157 0.01575 -0.0252 0.5599 0.0232
-11.000 -0.9465 0.02034 0.01432 -0.0231 0.5479 0.0234
-10.750 -0.9239 0.01978 0.01368 -0.0221 0.5429 0.0235
-10.500 -0.9009 0.01925 0.01305 -0.0211 0.5380 0.0236
-10.250 -0.8775 0.01875 0.01246 -0.0202 0.5333 0.0237
-10.000 -0.8537 0.01825 0.01189 -0.0193 0.5300 0.0238
-9.750 -0.8295 0.01779 0.01136 -0.0185 0.5260 0.0239
-9.500 -0.8048 0.01737 0.01086 -0.0178 0.5218 0.0240
-9.250 -0.7799 0.01698 0.01039 -0.0171 0.5176 0.0241
-9.000 -0.7557 0.01647 0.00981 -0.0162 0.5138 0.0242
-8.750 -0.7315 0.01593 0.00922 -0.0154 0.5116 0.0244
-8.500 -0.7064 0.01549 0.00874 -0.0147 0.5090 0.0246
-8.250 -0.6808 0.01511 0.00831 -0.0141 0.5060 0.0248
-8.000 -0.6548 0.01476 0.00792 -0.0135 0.5028 0.0250
-7.750 -0.6285 0.01445 0.00756 -0.0129 0.4994 0.0252
-7.500 -0.6020 0.01416 0.00723 -0.0124 0.4958 0.0254
-7.250 -0.5753 0.01388 0.00691 -0.0120 0.4937 0.0256
-7.000 -0.5484 0.01359 0.00660 -0.0115 0.4918 0.0259
-6.750 -0.5214 0.01332 0.00629 -0.0110 0.4895 0.0261
-6.500 -0.4943 0.01307 0.00601 -0.0106 0.4869 0.0263
-6.250 -0.4670 0.01283 0.00573 -0.0102 0.4840 0.0266
-6.000 -0.4397 0.01260 0.00546 -0.0098 0.4811 0.0269
-5.750 -0.4123 0.01240 0.00522 -0.0095 0.4783 0.0271
-5.500 -0.3846 0.01222 0.00500 -0.0091 0.4758 0.0274
-5.250 -0.3568 0.01202 0.00479 -0.0088 0.4743 0.0277
-5.000 -0.3294 0.01177 0.00452 -0.0085 0.4724 0.0280
-4.750 -0.3018 0.01154 0.00428 -0.0081 0.4701 0.0284
-4.500 -0.2740 0.01134 0.00407 -0.0078 0.4675 0.0289
-4.250 -0.2461 0.01117 0.00388 -0.0075 0.4649 0.0293
-4.000 -0.2182 0.01102 0.00371 -0.0073 0.4625 0.0298
-3.750 -0.1902 0.01088 0.00355 -0.0070 0.4600 0.0303
-3.500 -0.1621 0.01075 0.00340 -0.0068 0.4576 0.0308
-3.250 -0.1339 0.01061 0.00326 -0.0065 0.4561 0.0314
-3.000 -0.1057 0.01047 0.00312 -0.0063 0.4540 0.0320
-2.750 -0.0777 0.01032 0.00298 -0.0061 0.4517 0.0329
-2.500 -0.0495 0.01020 0.00286 -0.0059 0.4493 0.0340
-2.250 -0.0213 0.01010 0.00276 -0.0057 0.4470 0.0351
-2.000 0.0069 0.01000 0.00266 -0.0055 0.4447 0.0367
-1.750 0.0349 0.00991 0.00257 -0.0053 0.4420 0.0390
-1.500 0.0630 0.00982 0.00249 -0.0051 0.4395 0.0421
-1.250 0.0912 0.00971 0.00241 -0.0049 0.4377 0.0463
-1.000 0.1194 0.00961 0.00234 -0.0047 0.4357 0.0521
-0.750 0.1473 0.00950 0.00227 -0.0045 0.4332 0.0605
-0.500 0.1752 0.00940 0.00223 -0.0044 0.4301 0.0728
-0.250 0.2032 0.00934 0.00220 -0.0042 0.4263 0.0837
0.000 0.2314 0.00932 0.00217 -0.0041 0.4223 0.0909
0.250 0.2596 0.00925 0.00215 -0.0039 0.4192 0.0982
0.500 0.2879 0.00922 0.00212 -0.0038 0.4151 0.1035
0.750 0.3160 0.00919 0.00210 -0.0037 0.4109 0.1096
1.250 0.3719 0.00912 0.00208 -0.0034 0.4043 0.1300
1.500 0.3989 0.00899 0.00212 -0.0032 0.4016 0.1778
1.750 0.4269 0.00896 0.00215 -0.0031 0.3986 0.1987
2.000 0.4551 0.00897 0.00217 -0.0030 0.3953 0.2093
2.250 0.4831 0.00898 0.00220 -0.0029 0.3919 0.2182
2.500 0.5112 0.00902 0.00224 -0.0029 0.3887 0.2242
2.750 0.5394 0.00902 0.00227 -0.0028 0.3860 0.2332
3.250 0.5950 0.00903 0.00236 -0.0026 0.3789 0.2632
3.500 0.6220 0.00902 0.00243 -0.0024 0.3749 0.2978
3.750 0.6453 0.00874 0.00249 -0.0016 0.3714 0.4339
4.000 0.6458 0.00742 0.00258 0.0041 0.3685 0.9067
4.250 0.6778 0.00754 0.00272 0.0034 0.3626 0.9294
4.500 0.7097 0.00771 0.00286 0.0026 0.3566 0.9417
4.750 0.7398 0.00783 0.00297 0.0022 0.3510 0.9490
5.000 0.7685 0.00798 0.00310 0.0020 0.3451 0.9540
5.250 0.8040 0.00817 0.00326 0.0004 0.3398 0.9585
5.500 0.8339 0.00831 0.00339 -0.0001 0.3345 0.9625
5.750 0.8581 0.00849 0.00354 0.0007 0.3287 0.9675
6.000 0.8948 0.00870 0.00372 -0.0013 0.3228 0.9694
6.250 0.9278 0.00888 0.00388 -0.0025 0.3160 0.9705
6.500 0.9603 0.00912 0.00409 -0.0037 0.3088 0.9717
6.750 0.9926 0.00936 0.00429 -0.0049 0.3000 0.9734
7.000 1.0219 0.00963 0.00452 -0.0055 0.2914 0.9748
7.250 1.0498 0.00988 0.00473 -0.0058 0.2836 0.9763
7.500 1.0759 0.01015 0.00497 -0.0058 0.2764 0.9783
7.750 1.0998 0.01039 0.00520 -0.0053 0.2700 0.9809
8.000 1.1308 0.01073 0.00550 -0.0064 0.2625 0.9816
8.250 1.1610 0.01097 0.00573 -0.0073 0.2573 0.9823
8.500 1.1917 0.01127 0.00602 -0.0084 0.2518 0.9832
8.750 1.2229 0.01164 0.00636 -0.0096 0.2451 0.9845
9.000 1.2535 0.01197 0.00668 -0.0108 0.2388 0.9860
9.250 1.2808 0.01239 0.00707 -0.0114 0.2322 0.9876
9.500 1.3072 0.01270 0.00739 -0.0117 0.2284 0.9889
9.750 1.3329 0.01302 0.00771 -0.0119 0.2248 0.9904
10.000 1.3568 0.01339 0.00810 -0.0119 0.2214 0.9922
10.250 1.3825 0.01386 0.00856 -0.0124 0.2168 0.9934
10.500 1.4097 0.01427 0.00899 -0.0133 0.2127 0.9945
10.750 1.4364 0.01469 0.00943 -0.0140 0.2093 0.9958
11.000 1.4620 0.01521 0.00996 -0.0147 0.2059 0.9973
11.250 1.4862 0.01585 0.01061 -0.0155 0.2024 0.9988
11.500 1.4945 0.01676 0.01157 -0.0143 0.1996 1.0000
11.750 1.4881 0.01779 0.01266 -0.0104 0.1982 1.0000
12.000 1.4905 0.01883 0.01374 -0.0081 0.1962 1.0000
12.250 1.4938 0.02003 0.01497 -0.0062 0.1931 1.0000
12.500 1.4933 0.02164 0.01659 -0.0044 0.1883 1.0000
12.750 1.4943 0.02328 0.01825 -0.0030 0.1835 1.0000
13.000 1.4961 0.02497 0.01996 -0.0017 0.1774 1.0000
13.250 1.4909 0.02731 0.02228 -0.0005 0.1695 1.0000
13.500 1.4872 0.02964 0.02461 0.0005 0.1615 1.0000
13.750 1.4794 0.03239 0.02736 0.0014 0.1525 1.0000
14.000 1.4667 0.03565 0.03060 0.0023 0.1423 1.0000
14.500 1.4501 0.04175 0.03670 0.0033 0.1285 1.0000
14.750 1.4437 0.04479 0.03975 0.0036 0.1234 1.0000
15.000 1.4441 0.04719 0.04218 0.0038 0.1202 1.0000
15.250 1.4389 0.05024 0.04525 0.0039 0.1156 1.0000
15.500 1.4353 0.05313 0.04816 0.0039 0.1117 1.0000
15.750 1.4336 0.05592 0.05098 0.0039 0.1080 1.0000
16.000 1.4345 0.05843 0.05353 0.0038 0.1052 1.0000
16.250 1.4292 0.06169 0.05680 0.0036 0.1015 1.0000
16.500 1.4302 0.06426 0.05941 0.0034 0.0989 1.0000
16.750 1.4284 0.06722 0.06241 0.0031 0.0945 1.0000
17.000 1.4254 0.07031 0.06550 0.0028 0.0901 1.0000
17.500 1.3938 0.07978 0.07490 0.0013 0.0675 1.0000
17.750 1.3835 0.08396 0.07908 0.0006 0.0616 1.0000
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Polar data table (+)
Polar graphs
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