GOE 407 AIRFOIL (goe407-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 407 AIRFOIL (goe407-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.09 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe407-il-1000000-n5.txt Download as CSV file: xf-goe407-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 407 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
------ -------- --------- --------- -------- -------- --------
-10.500 -0.2790 0.10334 0.10154 -0.0495 0.9890 0.0118
-10.250 -0.2708 0.09968 0.09788 -0.0520 0.9876 0.0120
-10.000 -0.2718 0.09318 0.09138 -0.0563 0.9860 0.0132
-9.750 -0.2560 0.09105 0.08925 -0.0587 0.9848 0.0133
-9.500 -0.2482 0.08812 0.08633 -0.0605 0.9819 0.0134
-9.250 -0.2376 0.08588 0.08410 -0.0619 0.9788 0.0137
-9.000 -0.2272 0.08287 0.08109 -0.0645 0.9760 0.0139
-8.750 -0.2157 0.07957 0.07779 -0.0677 0.9735 0.0142
-8.500 -0.2120 0.07641 0.07464 -0.0696 0.9676 0.0143
-8.250 -0.2024 0.07252 0.07074 -0.0740 0.9618 0.0148
-8.000 -0.2073 0.06411 0.06229 -0.0834 0.9497 0.0160
-7.750 -0.1822 0.06118 0.05932 -0.0885 0.9409 0.0162
-7.500 -0.1425 0.05686 0.05492 -0.0983 0.9245 0.0164
-7.250 -0.0880 0.05200 0.04968 -0.1114 0.8515 0.0167
-7.000 -0.0819 0.04995 0.04738 -0.1109 0.8100 0.0170
-6.750 -0.0769 0.04691 0.04419 -0.1107 0.7906 0.0172
-6.500 -0.0683 0.04417 0.04132 -0.1104 0.7753 0.0177
-5.750 -0.0679 0.02670 0.02296 -0.1043 0.7377 0.0195
-5.500 -0.0515 0.02522 0.02132 -0.1027 0.7257 0.0197
-5.250 -0.0360 0.02348 0.01939 -0.1008 0.7125 0.0199
-5.000 -0.0230 0.02110 0.01676 -0.0983 0.6978 0.0202
-4.750 -0.0152 0.01754 0.01273 -0.0946 0.6835 0.0206
-4.500 0.0006 0.01584 0.01069 -0.0923 0.6695 0.0210
-4.250 0.0191 0.01461 0.00918 -0.0904 0.6566 0.0212
-4.000 0.0396 0.01369 0.00802 -0.0888 0.6459 0.0214
-3.750 0.0619 0.01294 0.00707 -0.0876 0.6367 0.0216
-3.500 0.0849 0.01233 0.00631 -0.0865 0.6292 0.0218
-3.250 0.1093 0.01188 0.00573 -0.0857 0.6228 0.0221
-3.000 0.1337 0.01151 0.00525 -0.0848 0.6173 0.0224
-2.750 0.1586 0.01112 0.00477 -0.0841 0.6121 0.0225
-2.500 0.1839 0.01081 0.00439 -0.0834 0.6069 0.0227
-2.250 0.2089 0.01052 0.00402 -0.0827 0.6017 0.0228
-2.000 0.2343 0.01036 0.00381 -0.0821 0.5966 0.0230
-1.750 0.2591 0.00992 0.00332 -0.0813 0.5910 0.0233
-1.500 0.2834 0.00964 0.00299 -0.0805 0.5843 0.0235
-1.250 0.3083 0.00943 0.00276 -0.0798 0.5785 0.0238
-1.000 0.3334 0.00925 0.00257 -0.0791 0.5723 0.0241
-0.750 0.3580 0.00913 0.00242 -0.0783 0.5652 0.0243
-0.500 0.3833 0.00900 0.00228 -0.0776 0.5589 0.0246
-0.250 0.4080 0.00889 0.00214 -0.0768 0.5516 0.0249
0.000 0.4329 0.00879 0.00202 -0.0761 0.5439 0.0251
0.250 0.4570 0.00872 0.00192 -0.0752 0.5323 0.0255
0.500 0.4812 0.00869 0.00184 -0.0743 0.5186 0.0259
0.750 0.5048 0.00869 0.00178 -0.0734 0.4997 0.0264
1.000 0.5279 0.00873 0.00174 -0.0723 0.4776 0.0268
1.250 0.5503 0.00882 0.00173 -0.0711 0.4546 0.0272
1.500 0.5719 0.00898 0.00176 -0.0697 0.4252 0.0275
1.750 0.5944 0.00909 0.00178 -0.0686 0.4048 0.0278
2.000 0.6175 0.00914 0.00177 -0.0675 0.3909 0.0289
2.250 0.6410 0.00921 0.00180 -0.0666 0.3777 0.0296
2.500 0.6645 0.00929 0.00184 -0.0656 0.3650 0.0304
2.750 0.6879 0.00938 0.00189 -0.0647 0.3530 0.0317
3.000 0.7113 0.00948 0.00195 -0.0637 0.3430 0.0329
3.250 0.7350 0.00954 0.00201 -0.0628 0.3339 0.0376
3.500 0.7575 0.00960 0.00212 -0.0617 0.3233 0.0754
4.000 0.8025 0.00971 0.00234 -0.0595 0.3042 0.1663
4.500 1.0285 0.00923 0.00349 -0.0994 0.2730 0.9984
4.750 1.0651 0.00941 0.00360 -0.1016 0.2628 1.0000
5.000 1.0875 0.00957 0.00374 -0.1005 0.2546 1.0000
5.250 1.1094 0.00976 0.00390 -0.0993 0.2475 1.0000
5.500 1.1318 0.00992 0.00404 -0.0982 0.2407 1.0000
5.750 1.1529 0.01014 0.00422 -0.0969 0.2316 1.0000
6.000 1.1744 0.01033 0.00440 -0.0957 0.2234 1.0000
6.250 1.1937 0.01064 0.00462 -0.0940 0.2073 1.0000
6.500 1.2128 0.01095 0.00486 -0.0924 0.1916 1.0000
6.750 1.2259 0.01156 0.00526 -0.0896 0.1525 1.0000
7.000 1.2361 0.01232 0.00580 -0.0864 0.1165 1.0000
7.250 1.2538 0.01266 0.00611 -0.0844 0.1091 1.0000
7.500 1.2718 0.01297 0.00640 -0.0826 0.1026 1.0000
7.750 1.2900 0.01325 0.00668 -0.0808 0.0982 1.0000
8.000 1.3069 0.01358 0.00700 -0.0788 0.0932 1.0000
8.250 1.3244 0.01386 0.00729 -0.0768 0.0890 1.0000
8.500 1.3418 0.01412 0.00757 -0.0749 0.0862 1.0000
8.750 1.3544 0.01446 0.00789 -0.0720 0.0801 1.0000
9.000 1.3666 0.01476 0.00819 -0.0691 0.0752 1.0000
9.250 1.3775 0.01513 0.00853 -0.0659 0.0684 1.0000
9.500 1.3887 0.01553 0.00890 -0.0629 0.0612 1.0000
9.750 1.3984 0.01602 0.00935 -0.0597 0.0527 1.0000
10.000 1.4047 0.01670 0.00995 -0.0560 0.0400 1.0000
10.250 1.4029 0.01780 0.01092 -0.0511 0.0200 1.0000
10.500 1.4116 0.01845 0.01159 -0.0481 0.0162 1.0000
10.750 1.4220 0.01905 0.01221 -0.0454 0.0147 1.0000
11.000 1.4323 0.01968 0.01288 -0.0428 0.0133 1.0000
11.250 1.4431 0.02030 0.01354 -0.0404 0.0125 1.0000
11.500 1.4534 0.02098 0.01426 -0.0380 0.0120 1.0000
11.750 1.4621 0.02177 0.01510 -0.0355 0.0111 1.0000
12.000 1.4699 0.02266 0.01603 -0.0330 0.0104 1.0000
12.250 1.4797 0.02347 0.01689 -0.0310 0.0102 1.0000
12.500 1.4886 0.02439 0.01787 -0.0289 0.0098 1.0000
12.750 1.4969 0.02538 0.01892 -0.0269 0.0095 1.0000
13.000 1.5039 0.02653 0.02013 -0.0250 0.0090 1.0000
13.250 1.5106 0.02778 0.02144 -0.0232 0.0088 1.0000
13.500 1.5165 0.02914 0.02285 -0.0216 0.0084 1.0000
13.750 1.5212 0.03067 0.02444 -0.0199 0.0081 1.0000
14.000 1.5241 0.03242 0.02627 -0.0184 0.0078 1.0000
14.250 1.5298 0.03399 0.02791 -0.0172 0.0076 1.0000
14.500 1.5332 0.03581 0.02981 -0.0160 0.0076 1.0000
14.750 1.5373 0.03764 0.03171 -0.0150 0.0073 1.0000
15.000 1.5403 0.03965 0.03379 -0.0141 0.0071 1.0000
15.250 1.5416 0.04189 0.03612 -0.0133 0.0070 1.0000
15.500 1.5431 0.04416 0.03846 -0.0126 0.0067 1.0000
15.750 1.5434 0.04662 0.04100 -0.0121 0.0066 1.0000
16.000 1.5421 0.04933 0.04379 -0.0116 0.0064 1.0000
16.250 1.5392 0.05229 0.04682 -0.0113 0.0063 1.0000
16.500 1.5358 0.05537 0.04999 -0.0111 0.0062 1.0000
16.750 1.5312 0.05869 0.05340 -0.0111 0.0060 1.0000
17.000 1.5242 0.06244 0.05725 -0.0113 0.0060 1.0000
17.250 1.5147 0.06659 0.06150 -0.0118 0.0057 1.0000
17.500 1.5063 0.07076 0.06577 -0.0124 0.0057 1.0000
17.750 1.5003 0.07469 0.06980 -0.0130 0.0057 1.0000
18.000 1.4919 0.07907 0.07428 -0.0140 0.0056 1.0000
18.250 1.4832 0.08354 0.07886 -0.0150 0.0056 1.0000
18.500 1.4752 0.08800 0.08342 -0.0162 0.0055 1.0000
18.750 1.4623 0.09331 0.08883 -0.0177 0.0055 1.0000
19.000 1.4489 0.09874 0.09438 -0.0193 0.0055 1.0000
19.250 1.4408 0.10335 0.09908 -0.0208 0.0054 1.0000
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