GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
|---|---|
|
Airfoil: GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.32 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe314-il-1000000-n5.txt Download as CSV file: xf-goe314-il-1000000-n5.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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3480 0.08992 0.08829 -0.0231 0.9999 0.0127
-8.500 -0.3369 0.08592 0.08429 -0.0270 0.9928 0.0131
-8.250 -0.3389 0.07990 0.07827 -0.0320 0.9781 0.0144
-8.000 -0.3108 0.07619 0.07453 -0.0394 0.9568 0.0145
-7.750 -0.2625 0.07137 0.06965 -0.0520 0.9404 0.0148
-7.500 -0.2087 0.06592 0.06399 -0.0666 0.8966 0.0154
-7.250 -0.1980 0.06303 0.06087 -0.0691 0.8478 0.0158
-7.000 -0.2007 0.05554 0.05320 -0.0746 0.8237 0.0174
-6.750 -0.1874 0.05307 0.05062 -0.0759 0.8065 0.0176
-6.500 -0.1718 0.05074 0.04820 -0.0771 0.7923 0.0178
-6.250 -0.1543 0.04892 0.04629 -0.0778 0.7768 0.0179
-6.000 -0.1361 0.04684 0.04412 -0.0787 0.7643 0.0182
-5.750 -0.1174 0.04451 0.04168 -0.0797 0.7515 0.0184
-5.500 -0.0978 0.04228 0.03934 -0.0804 0.7376 0.0189
-5.250 -0.0777 0.03955 0.03646 -0.0813 0.7233 0.0195
-5.000 -0.0577 0.03593 0.03264 -0.0821 0.7077 0.0200
-4.750 -0.0398 0.02889 0.02519 -0.0827 0.6948 0.0211
-4.500 -0.0190 0.02655 0.02262 -0.0824 0.6761 0.0215
-4.250 0.0035 0.02505 0.02094 -0.0820 0.6543 0.0217
-4.000 0.0262 0.02367 0.01935 -0.0814 0.6284 0.0220
-3.750 0.0490 0.02238 0.01783 -0.0807 0.5990 0.0223
-3.500 0.0718 0.02064 0.01583 -0.0800 0.5736 0.0226
-3.250 0.0864 0.01274 0.00690 -0.0777 0.5587 0.0246
-3.000 0.1107 0.01180 0.00566 -0.0770 0.5340 0.0250
-2.750 0.1362 0.01136 0.00502 -0.0765 0.5134 0.0253
-2.500 0.1622 0.01103 0.00455 -0.0760 0.4962 0.0254
-2.250 0.1878 0.01053 0.00389 -0.0755 0.4812 0.0258
-2.000 0.2136 0.01016 0.00340 -0.0750 0.4671 0.0262
-1.750 0.2400 0.00995 0.00312 -0.0745 0.4545 0.0265
-1.500 0.2665 0.00980 0.00290 -0.0741 0.4445 0.0268
-1.250 0.2930 0.00968 0.00272 -0.0737 0.4337 0.0271
-1.000 0.3193 0.00958 0.00255 -0.0733 0.4211 0.0274
-0.750 0.3458 0.00948 0.00240 -0.0729 0.4100 0.0278
-0.500 0.3722 0.00940 0.00226 -0.0725 0.3994 0.0283
-0.250 0.3988 0.00935 0.00216 -0.0721 0.3894 0.0289
0.000 0.4254 0.00930 0.00207 -0.0717 0.3805 0.0296
0.500 0.4786 0.00920 0.00189 -0.0710 0.3642 0.0305
0.750 0.5050 0.00917 0.00182 -0.0706 0.3561 0.0309
1.000 0.5316 0.00909 0.00172 -0.0702 0.3495 0.0319
1.250 0.5583 0.00908 0.00170 -0.0698 0.3427 0.0327
1.500 0.5850 0.00909 0.00170 -0.0695 0.3365 0.0336
1.750 0.6114 0.00913 0.00171 -0.0691 0.3256 0.0347
2.000 0.6377 0.00919 0.00172 -0.0687 0.3131 0.0359
2.250 0.6640 0.00927 0.00176 -0.0684 0.3014 0.0369
2.500 0.6902 0.00933 0.00179 -0.0680 0.2924 0.0398
2.750 0.7167 0.00939 0.00184 -0.0676 0.2837 0.0422
3.000 0.7429 0.00948 0.00191 -0.0673 0.2746 0.0441
3.250 0.7688 0.00959 0.00197 -0.0668 0.2627 0.0474
3.500 0.7945 0.00972 0.00207 -0.0664 0.2491 0.0509
3.750 0.8198 0.00991 0.00218 -0.0659 0.2328 0.0538
4.000 0.8450 0.01008 0.00231 -0.0654 0.2174 0.0616
4.250 0.8702 0.01023 0.00247 -0.0649 0.2042 0.1012
4.750 0.9452 0.00911 0.00306 -0.0700 0.1779 1.0000
5.000 0.9689 0.00931 0.00322 -0.0692 0.1700 1.0000
5.250 0.9923 0.00954 0.00339 -0.0683 0.1620 1.0000
5.500 1.0161 0.00974 0.00356 -0.0675 0.1552 1.0000
5.750 1.0395 0.00999 0.00375 -0.0667 0.1473 1.0000
6.000 1.0633 0.01020 0.00394 -0.0659 0.1400 1.0000
6.250 1.0851 0.01059 0.00421 -0.0648 0.1213 1.0000
6.500 1.0998 0.01163 0.00492 -0.0627 0.0611 1.0000
6.750 1.1227 0.01194 0.00522 -0.0618 0.0568 1.0000
7.000 1.1456 0.01224 0.00551 -0.0609 0.0532 1.0000
7.250 1.1689 0.01251 0.00578 -0.0601 0.0507 1.0000
7.500 1.1925 0.01274 0.00603 -0.0594 0.0499 1.0000
7.750 1.2159 0.01299 0.00631 -0.0587 0.0487 1.0000
8.000 1.2389 0.01327 0.00660 -0.0579 0.0472 1.0000
8.250 1.2613 0.01358 0.00692 -0.0571 0.0452 1.0000
8.500 1.2834 0.01393 0.00727 -0.0561 0.0431 1.0000
8.750 1.3053 0.01427 0.00763 -0.0552 0.0411 1.0000
9.000 1.3279 0.01453 0.00792 -0.0544 0.0401 1.0000
9.250 1.3500 0.01483 0.00823 -0.0536 0.0379 1.0000
9.500 1.3705 0.01525 0.00862 -0.0525 0.0334 1.0000
10.000 1.4050 0.01649 0.00974 -0.0494 0.0146 1.0000
10.250 1.4236 0.01697 0.01025 -0.0481 0.0131 1.0000
10.500 1.4411 0.01749 0.01079 -0.0466 0.0119 1.0000
10.750 1.4572 0.01806 0.01141 -0.0449 0.0108 1.0000
11.000 1.4732 0.01854 0.01194 -0.0431 0.0103 1.0000
11.250 1.4867 0.01905 0.01249 -0.0409 0.0098 1.0000
11.500 1.4988 0.01960 0.01309 -0.0385 0.0093 1.0000
11.750 1.5099 0.02023 0.01375 -0.0361 0.0089 1.0000
12.000 1.5198 0.02093 0.01452 -0.0337 0.0085 1.0000
12.250 1.5287 0.02172 0.01536 -0.0313 0.0081 1.0000
12.500 1.5369 0.02259 0.01629 -0.0290 0.0078 1.0000
12.750 1.5459 0.02345 0.01722 -0.0269 0.0076 1.0000
13.000 1.5539 0.02442 0.01826 -0.0250 0.0074 1.0000
13.250 1.5611 0.02552 0.01942 -0.0232 0.0071 1.0000
13.500 1.5665 0.02681 0.02080 -0.0214 0.0069 1.0000
13.750 1.5714 0.02826 0.02230 -0.0199 0.0066 1.0000
14.000 1.5742 0.02997 0.02410 -0.0186 0.0064 1.0000
14.250 1.5768 0.03184 0.02604 -0.0175 0.0062 1.0000
14.500 1.5760 0.03417 0.02845 -0.0166 0.0061 1.0000
14.750 1.5737 0.03681 0.03119 -0.0161 0.0058 1.0000
15.000 1.5694 0.03986 0.03435 -0.0159 0.0058 1.0000
15.250 1.5659 0.04303 0.03762 -0.0160 0.0057 1.0000
15.500 1.5627 0.04633 0.04102 -0.0165 0.0056 1.0000
15.750 1.5555 0.05033 0.04514 -0.0173 0.0056 1.0000
16.000 1.5471 0.05464 0.04957 -0.0184 0.0055 1.0000
16.250 1.5378 0.05920 0.05424 -0.0198 0.0055 1.0000
16.500 1.5241 0.06449 0.05966 -0.0214 0.0055 1.0000
16.750 1.5118 0.06971 0.06499 -0.0231 0.0054 1.0000
17.000 1.4984 0.07513 0.07052 -0.0250 0.0053 1.0000
17.250 1.4826 0.08105 0.07655 -0.0271 0.0053 1.0000
17.500 1.4670 0.08704 0.08266 -0.0294 0.0053 1.0000
|
Polar data table (+)
Polar graphs
<< Back to GOE 314 (HANSA-BRANDENBURG) AIRFOIL (goe314-il)