GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.1 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe314-il-1000000.txt Download as CSV file: xf-goe314-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 314 (HANSA-BRANDENBURG) 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 = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.250 -0.3256 0.09037 0.08878 -0.0226 1.0000 0.0197
-8.000 -0.3316 0.08784 0.08628 -0.0229 1.0000 0.0198
-7.750 -0.3460 0.08573 0.08421 -0.0220 1.0000 0.0198
-7.500 -0.3229 0.08023 0.07870 -0.0310 0.9972 0.0199
-7.250 -0.3050 0.07574 0.07421 -0.0337 0.9940 0.0202
-6.250 -0.2030 0.06186 0.06023 -0.0544 0.9590 0.0225
-6.000 -0.1409 0.05362 0.05176 -0.0725 0.9430 0.0238
-5.250 -0.0643 0.04374 0.04141 -0.0819 0.8557 0.0246
-5.000 -0.0457 0.04183 0.03936 -0.0822 0.8365 0.0250
-4.750 -0.0259 0.03981 0.03721 -0.0825 0.8201 0.0256
-4.500 0.0031 0.03676 0.03389 -0.0836 0.8059 0.0281
-4.250 0.0257 0.03414 0.03108 -0.0835 0.7927 0.0283
-4.000 0.0423 0.02948 0.02616 -0.0834 0.7804 0.0286
-3.750 0.0629 0.02797 0.02454 -0.0830 0.7668 0.0289
-3.500 0.0848 0.02672 0.02318 -0.0826 0.7520 0.0292
-3.250 0.1074 0.02548 0.02182 -0.0821 0.7358 0.0295
-3.000 0.1306 0.02425 0.02045 -0.0816 0.7184 0.0301
-2.750 0.1544 0.02298 0.01902 -0.0810 0.6989 0.0312
-2.500 0.1832 0.02154 0.01720 -0.0796 0.6772 0.0336
-2.250 0.2062 0.01985 0.01521 -0.0786 0.6518 0.0337
-1.500 -0.1181 0.01499 0.01176 0.0201 0.6060 0.0336
-1.000 0.3223 0.01207 0.00595 -0.0739 0.5162 0.0329
-0.750 0.3477 0.01143 0.00508 -0.0732 0.4954 0.0332
-0.500 0.3737 0.01112 0.00462 -0.0726 0.4768 0.0335
-0.250 0.3997 0.01073 0.00409 -0.0721 0.4612 0.0338
0.000 0.4249 0.00998 0.00320 -0.0714 0.4473 0.0342
0.500 0.4772 0.00955 0.00271 -0.0705 0.4261 0.0359
0.750 0.5035 0.00947 0.00260 -0.0701 0.4173 0.0370
1.000 0.5299 0.00934 0.00244 -0.0697 0.4091 0.0380
1.250 0.5561 0.00926 0.00232 -0.0692 0.4012 0.0389
1.500 0.5827 0.00921 0.00224 -0.0688 0.3928 0.0398
1.750 0.6085 0.00909 0.00208 -0.0683 0.3832 0.0408
2.000 0.6345 0.00899 0.00196 -0.0678 0.3739 0.0429
2.250 0.6611 0.00899 0.00195 -0.0675 0.3664 0.0451
2.500 0.6875 0.00903 0.00196 -0.0671 0.3579 0.0473
2.750 0.7139 0.00900 0.00191 -0.0667 0.3500 0.0500
3.250 0.7666 0.00907 0.00194 -0.0659 0.3324 0.0577
3.500 0.7926 0.00912 0.00198 -0.0655 0.3239 0.0669
3.750 0.8188 0.00910 0.00206 -0.0651 0.3160 0.1210
4.000 0.8786 0.00764 0.00239 -0.0729 0.3010 1.0000
4.250 0.9025 0.00780 0.00248 -0.0720 0.2917 1.0000
4.500 0.9265 0.00796 0.00259 -0.0712 0.2814 1.0000
4.750 0.9505 0.00813 0.00271 -0.0704 0.2707 1.0000
5.000 0.9743 0.00832 0.00284 -0.0695 0.2598 1.0000
5.250 0.9978 0.00853 0.00299 -0.0686 0.2477 1.0000
5.500 1.0211 0.00877 0.00315 -0.0678 0.2345 1.0000
5.750 1.0446 0.00900 0.00332 -0.0669 0.2220 1.0000
6.000 1.0677 0.00926 0.00351 -0.0660 0.2088 1.0000
6.250 1.0907 0.00953 0.00372 -0.0651 0.1959 1.0000
6.500 1.1135 0.00983 0.00396 -0.0642 0.1826 1.0000
6.750 1.1362 0.01015 0.00420 -0.0633 0.1696 1.0000
7.000 1.1588 0.01047 0.00445 -0.0624 0.1571 1.0000
7.250 1.1812 0.01082 0.00473 -0.0614 0.1431 1.0000
7.500 1.2016 0.01134 0.00510 -0.0602 0.1181 1.0000
7.750 1.2145 0.01252 0.00595 -0.0579 0.0631 1.0000
8.000 1.2362 0.01292 0.00634 -0.0569 0.0591 1.0000
8.250 1.2580 0.01331 0.00673 -0.0559 0.0554 1.0000
8.500 1.2805 0.01361 0.00707 -0.0550 0.0537 1.0000
8.750 1.3031 0.01390 0.00740 -0.0542 0.0524 1.0000
9.000 1.3250 0.01424 0.00778 -0.0533 0.0506 1.0000
9.250 1.3460 0.01465 0.00820 -0.0522 0.0484 1.0000
9.500 1.3659 0.01512 0.00869 -0.0510 0.0453 1.0000
9.750 1.3876 0.01542 0.00903 -0.0501 0.0436 1.0000
10.000 1.4098 0.01568 0.00931 -0.0493 0.0410 1.0000
10.250 1.4290 0.01614 0.00974 -0.0481 0.0357 1.0000
10.500 1.4455 0.01677 0.01023 -0.0465 0.0223 1.0000
10.750 1.4603 0.01747 0.01092 -0.0446 0.0177 1.0000
11.000 1.4743 0.01819 0.01165 -0.0425 0.0158 1.0000
11.250 1.4878 0.01878 0.01230 -0.0403 0.0149 1.0000
11.500 1.4988 0.01939 0.01297 -0.0377 0.0142 1.0000
11.750 1.5083 0.02009 0.01374 -0.0350 0.0137 1.0000
12.000 1.5155 0.02093 0.01464 -0.0321 0.0130 1.0000
12.250 1.5191 0.02201 0.01580 -0.0290 0.0124 1.0000
12.500 1.5244 0.02305 0.01692 -0.0263 0.0120 1.0000
12.750 1.5329 0.02395 0.01790 -0.0243 0.0117 1.0000
13.000 1.5389 0.02508 0.01911 -0.0222 0.0114 1.0000
13.250 1.5426 0.02646 0.02057 -0.0202 0.0110 1.0000
13.500 1.5462 0.02796 0.02215 -0.0185 0.0108 1.0000
13.750 1.5474 0.02979 0.02407 -0.0170 0.0106 1.0000
14.000 1.5470 0.03193 0.02630 -0.0159 0.0104 1.0000
14.250 1.5430 0.03459 0.02906 -0.0150 0.0101 1.0000
14.500 1.5378 0.03762 0.03220 -0.0146 0.0099 1.0000
14.750 1.5245 0.04185 0.03656 -0.0147 0.0097 1.0000
15.000 1.5181 0.04557 0.04039 -0.0153 0.0097 1.0000
15.250 1.4969 0.05150 0.04648 -0.0168 0.0095 1.0000
15.500 1.4834 0.05664 0.05175 -0.0183 0.0095 1.0000
15.750 1.4725 0.06151 0.05674 -0.0198 0.0094 1.0000
16.000 1.4607 0.06659 0.06192 -0.0214 0.0094 1.0000
16.250 1.4503 0.07156 0.06700 -0.0230 0.0093 1.0000
16.500 1.4382 0.07681 0.07235 -0.0247 0.0093 1.0000
16.750 1.4271 0.08202 0.07767 -0.0266 0.0092 1.0000
17.000 1.4133 0.08775 0.08350 -0.0287 0.0092 1.0000
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Polar data table (+)
Polar graphs
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