GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 315 (HANSA-BRANDENBURG III.5) AIRFOIL (goe315-il) Reynolds number: 1,000,000 Max Cl/Cd: 104.55 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe315-il-1000000.txt Download as CSV file: xf-goe315-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 315 (HANSA-BRANDENBURG III.5) 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
------ -------- --------- --------- -------- -------- --------
-9.000 -0.3849 0.09639 0.09474 -0.0159 1.0000 0.0156
-8.750 -0.3842 0.09283 0.09121 -0.0181 1.0000 0.0156
-8.500 -0.3837 0.08946 0.08786 -0.0200 1.0000 0.0156
-8.250 -0.3805 0.08578 0.08419 -0.0194 1.0000 0.0159
-8.000 -0.3789 0.08312 0.08156 -0.0197 1.0000 0.0159
-7.750 -0.3789 0.08084 0.07931 -0.0197 1.0000 0.0160
-7.500 -0.3755 0.07816 0.07664 -0.0209 1.0000 0.0162
-7.250 -0.3700 0.07535 0.07385 -0.0225 1.0000 0.0164
-7.000 -0.3520 0.07178 0.07028 -0.0273 0.9965 0.0168
-6.750 -0.3263 0.06729 0.06575 -0.0343 0.9756 0.0176
-6.500 -0.2589 0.05659 0.05479 -0.0567 0.9436 0.0190
-5.750 -0.2018 0.04666 0.04413 -0.0630 0.7924 0.0197
-5.500 -0.1840 0.04444 0.04177 -0.0634 0.7749 0.0200
-5.250 -0.1645 0.04212 0.03931 -0.0639 0.7615 0.0206
-5.000 -0.1359 0.03843 0.03532 -0.0647 0.7509 0.0229
-4.750 -0.1136 0.03539 0.03206 -0.0646 0.7408 0.0230
-4.500 -0.0976 0.03051 0.02693 -0.0647 0.7321 0.0233
-4.250 -0.0765 0.02888 0.02518 -0.0645 0.7226 0.0236
-4.000 -0.0539 0.02754 0.02376 -0.0643 0.7134 0.0239
-3.750 -0.0306 0.02616 0.02226 -0.0641 0.7043 0.0244
-3.500 -0.0065 0.02473 0.02070 -0.0637 0.6943 0.0252
-3.250 0.0234 0.02330 0.01892 -0.0625 0.6835 0.0277
-3.000 0.0476 0.02153 0.01689 -0.0617 0.6709 0.0278
-2.750 0.0678 0.01805 0.01315 -0.0611 0.6574 0.0286
-2.500 0.0927 0.01719 0.01218 -0.0607 0.6411 0.0290
-2.250 0.1180 0.01643 0.01129 -0.0603 0.6224 0.0296
-2.000 0.1434 0.01572 0.01041 -0.0598 0.6008 0.0306
-1.750 0.1711 0.01589 0.01035 -0.0591 0.5789 0.0335
-1.500 0.1976 0.01548 0.00970 -0.0585 0.5631 0.0338
-1.250 0.2211 0.01298 0.00701 -0.0579 0.5529 0.0356
-1.000 0.2477 0.01250 0.00647 -0.0577 0.5441 0.0365
-0.750 0.2744 0.01210 0.00598 -0.0573 0.5361 0.0380
-0.500 0.3018 0.01186 0.00566 -0.0570 0.5289 0.0400
-0.250 0.3296 0.01248 0.00618 -0.0566 0.5212 0.0415
0.000 0.3555 0.00992 0.00345 -0.0557 0.5155 0.0327
0.250 0.3819 0.00946 0.00293 -0.0552 0.5082 0.0324
0.500 0.4086 0.00917 0.00261 -0.0548 0.5011 0.0328
0.750 0.4352 0.00897 0.00238 -0.0544 0.4931 0.0331
1.000 0.4619 0.00879 0.00218 -0.0541 0.4862 0.0333
1.250 0.4884 0.00867 0.00202 -0.0537 0.4758 0.0335
1.500 0.5155 0.00857 0.00192 -0.0534 0.4679 0.0338
1.750 0.5415 0.00832 0.00161 -0.0529 0.4588 0.0352
2.000 0.5684 0.00823 0.00150 -0.0526 0.4467 0.0362
2.250 0.5952 0.00821 0.00145 -0.0523 0.4329 0.0376
2.500 0.6220 0.00824 0.00143 -0.0520 0.4162 0.0392
2.750 0.6483 0.00833 0.00143 -0.0517 0.3923 0.0408
3.000 0.6741 0.00848 0.00146 -0.0513 0.3626 0.0441
3.250 0.6981 0.00840 0.00162 -0.0507 0.3304 0.2477
3.500 0.7517 0.00719 0.00193 -0.0572 0.2839 1.0000
3.750 0.7755 0.00749 0.00209 -0.0565 0.2583 1.0000
4.000 0.7993 0.00779 0.00225 -0.0557 0.2359 1.0000
4.250 0.8234 0.00807 0.00242 -0.0550 0.2162 1.0000
4.500 0.8477 0.00832 0.00259 -0.0543 0.1992 1.0000
4.750 0.8710 0.00867 0.00278 -0.0535 0.1732 1.0000
5.000 0.8875 0.00974 0.00337 -0.0517 0.0828 1.0000
5.250 0.9083 0.01039 0.00381 -0.0505 0.0417 1.0000
5.500 0.9322 0.01070 0.00408 -0.0498 0.0361 1.0000
5.750 0.9567 0.01095 0.00433 -0.0491 0.0341 1.0000
6.000 0.9810 0.01121 0.00461 -0.0485 0.0333 1.0000
6.250 1.0051 0.01149 0.00493 -0.0478 0.0323 1.0000
6.500 1.0289 0.01182 0.00528 -0.0471 0.0313 1.0000
6.750 1.0523 0.01217 0.00565 -0.0463 0.0304 1.0000
7.000 1.0753 0.01257 0.00608 -0.0455 0.0295 1.0000
7.250 1.0974 0.01305 0.00661 -0.0446 0.0285 1.0000
7.500 1.1181 0.01367 0.00730 -0.0435 0.0275 1.0000
7.750 1.1411 0.01402 0.00768 -0.0427 0.0272 1.0000
8.000 1.1635 0.01443 0.00812 -0.0419 0.0267 1.0000
8.250 1.1853 0.01487 0.00861 -0.0410 0.0262 1.0000
8.500 1.2066 0.01534 0.00912 -0.0400 0.0254 1.0000
8.750 1.2274 0.01584 0.00966 -0.0390 0.0247 1.0000
9.000 1.2472 0.01640 0.01026 -0.0379 0.0240 1.0000
9.250 1.2657 0.01703 0.01093 -0.0366 0.0233 1.0000
9.500 1.2798 0.01798 0.01192 -0.0347 0.0225 1.0000
9.750 1.2887 0.01925 0.01328 -0.0322 0.0217 1.0000
10.000 1.3088 0.01963 0.01370 -0.0311 0.0214 1.0000
10.250 1.3271 0.02010 0.01423 -0.0299 0.0209 1.0000
10.500 1.3437 0.02065 0.01483 -0.0284 0.0203 1.0000
10.750 1.3587 0.02117 0.01539 -0.0266 0.0197 1.0000
11.000 1.3696 0.02180 0.01606 -0.0242 0.0192 1.0000
11.250 1.3820 0.02237 0.01666 -0.0222 0.0187 1.0000
11.500 1.3920 0.02310 0.01744 -0.0201 0.0182 1.0000
11.750 1.3966 0.02422 0.01860 -0.0176 0.0178 1.0000
12.000 1.3839 0.02672 0.02121 -0.0141 0.0172 1.0000
12.250 1.3963 0.02760 0.02216 -0.0131 0.0170 1.0000
12.500 1.4081 0.02862 0.02325 -0.0123 0.0167 1.0000
12.750 1.4175 0.02992 0.02462 -0.0116 0.0163 1.0000
13.000 1.4274 0.03127 0.02606 -0.0111 0.0158 1.0000
13.250 1.4397 0.03247 0.02731 -0.0108 0.0153 1.0000
13.500 1.4492 0.03398 0.02888 -0.0106 0.0149 1.0000
13.750 1.4580 0.03562 0.03057 -0.0105 0.0146 1.0000
14.000 1.4621 0.03780 0.03281 -0.0104 0.0144 1.0000
14.250 1.4667 0.04001 0.03508 -0.0105 0.0140 1.0000
14.500 1.4605 0.04346 0.03861 -0.0108 0.0137 1.0000
14.750 1.4484 0.04765 0.04293 -0.0111 0.0135 1.0000
15.000 1.4531 0.05011 0.04547 -0.0116 0.0133 1.0000
15.250 1.4557 0.05285 0.04830 -0.0122 0.0130 1.0000
15.500 1.4518 0.05637 0.05193 -0.0129 0.0129 1.0000
15.750 1.4508 0.05962 0.05527 -0.0138 0.0126 1.0000
16.000 1.4492 0.06304 0.05878 -0.0147 0.0123 1.0000
16.250 1.4454 0.06685 0.06268 -0.0159 0.0122 1.0000
16.500 1.4424 0.07065 0.06656 -0.0171 0.0119 1.0000
16.750 1.4409 0.07435 0.07034 -0.0185 0.0117 1.0000
17.000 1.4344 0.07879 0.07488 -0.0201 0.0116 1.0000
17.250 1.4349 0.08245 0.07859 -0.0216 0.0113 1.0000
17.500 1.4251 0.08751 0.08375 -0.0235 0.0113 1.0000
17.750 1.4180 0.09238 0.08870 -0.0255 0.0111 1.0000
18.000 1.4105 0.09744 0.09382 -0.0277 0.0109 1.0000
18.250 1.4004 0.10288 0.09934 -0.0301 0.0107 1.0000
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Polar data table (+)
Polar graphs
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