GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 318 (HANSA-BRANDENBURG VI.5) AIRFOIL (goe318-il) Reynolds number: 1,000,000 Max Cl/Cd: 113.89 at α=7.75° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe318-il-1000000.txt Download as CSV file: xf-goe318-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 318 (HANSA-BRANDENBURG VI.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 -0.3743 0.09493 0.09270 0.0061 0.7067 0.0161
-8.750 -0.3740 0.09057 0.08833 0.0047 0.7007 0.0161
-8.500 -0.4778 0.09916 0.09691 0.0152 0.7204 0.0161
-8.250 -0.4743 0.09502 0.09273 0.0126 0.7124 0.0161
-8.000 -0.4713 0.09071 0.08842 0.0096 0.7047 0.0161
-7.750 -0.3585 0.07703 0.07472 0.0023 0.6775 0.0172
-7.500 -0.3557 0.07363 0.07132 0.0010 0.6724 0.0176
-7.250 -0.3547 0.06992 0.06758 -0.0009 0.6679 0.0182
-7.000 -0.4318 0.07672 0.07431 -0.0021 0.6786 0.0173
-6.750 -0.3515 0.05685 0.05447 -0.0155 0.6615 0.0199
-6.500 -0.3407 0.05071 0.04826 -0.0205 0.6577 0.0199
-6.250 -0.3277 0.04403 0.04147 -0.0253 0.6542 0.0200
-4.750 -0.2133 0.01513 0.01150 -0.0379 0.6288 0.0255
-4.500 -0.1894 0.01419 0.01048 -0.0382 0.6239 0.0259
-4.250 -0.1648 0.01306 0.00926 -0.0385 0.6195 0.0266
-4.000 -0.1395 0.01152 0.00758 -0.0388 0.6150 0.0278
-3.750 -0.1094 0.01045 0.00611 -0.0383 0.6103 0.0306
-3.500 -0.0836 0.00883 0.00417 -0.0384 0.6061 0.0307
-2.750 -0.0064 0.01454 0.00870 -0.0397 0.5974 0.0314
-2.500 0.0223 0.01376 0.00775 -0.0397 0.5918 0.0312
-2.250 0.0511 0.01307 0.00696 -0.0397 0.5864 0.0311
-2.000 0.0799 0.01244 0.00623 -0.0398 0.5802 0.0310
-1.750 0.1087 0.01179 0.00547 -0.0398 0.5741 0.0309
-1.500 0.1374 0.01098 0.00459 -0.0398 0.5680 0.0310
-1.250 0.1658 0.01010 0.00366 -0.0399 0.5624 0.0318
-1.000 0.1945 0.00968 0.00322 -0.0400 0.5570 0.0325
-0.750 0.2233 0.00937 0.00290 -0.0401 0.5508 0.0331
-0.250 0.2811 0.00892 0.00240 -0.0403 0.5378 0.0344
0.000 0.3100 0.00875 0.00219 -0.0404 0.5303 0.0350
0.250 0.3390 0.00858 0.00201 -0.0405 0.5227 0.0356
0.500 0.3680 0.00847 0.00185 -0.0406 0.5141 0.0365
0.750 0.3970 0.00838 0.00176 -0.0408 0.5048 0.0376
1.000 0.4260 0.00834 0.00168 -0.0409 0.4951 0.0384
1.250 0.4551 0.00820 0.00148 -0.0411 0.4842 0.0411
1.500 0.4841 0.00817 0.00142 -0.0412 0.4725 0.0439
1.750 0.5130 0.00817 0.00139 -0.0414 0.4601 0.0474
2.000 0.5420 0.00802 0.00140 -0.0417 0.4469 0.1333
2.250 0.5658 0.00602 0.00152 -0.0414 0.4340 1.0000
2.500 0.5945 0.00616 0.00156 -0.0416 0.4193 1.0000
2.750 0.6232 0.00631 0.00163 -0.0417 0.4042 1.0000
3.000 0.6519 0.00647 0.00170 -0.0419 0.3881 1.0000
3.250 0.6805 0.00666 0.00179 -0.0421 0.3699 1.0000
3.500 0.7089 0.00688 0.00190 -0.0423 0.3498 1.0000
3.750 0.7373 0.00711 0.00203 -0.0426 0.3269 1.0000
4.000 0.7655 0.00739 0.00218 -0.0428 0.3047 1.0000
4.250 0.7937 0.00764 0.00234 -0.0430 0.2867 1.0000
4.500 0.8220 0.00787 0.00251 -0.0432 0.2742 1.0000
4.750 0.8502 0.00809 0.00268 -0.0434 0.2651 1.0000
5.000 0.8784 0.00827 0.00283 -0.0436 0.2587 1.0000
5.250 0.9066 0.00847 0.00301 -0.0437 0.2531 1.0000
5.500 0.9346 0.00868 0.00320 -0.0439 0.2478 1.0000
5.750 0.9628 0.00883 0.00335 -0.0441 0.2434 1.0000
6.000 0.9907 0.00904 0.00354 -0.0443 0.2381 1.0000
6.250 1.0185 0.00925 0.00374 -0.0444 0.2325 1.0000
6.500 1.0465 0.00939 0.00391 -0.0446 0.2295 1.0000
6.750 1.0743 0.00959 0.00410 -0.0447 0.2247 1.0000
7.000 1.1018 0.00983 0.00434 -0.0449 0.2183 1.0000
7.250 1.1296 0.00997 0.00451 -0.0450 0.2145 1.0000
7.500 1.1570 0.01020 0.00473 -0.0452 0.2079 1.0000
7.750 1.1844 0.01040 0.00495 -0.0453 0.2014 1.0000
8.000 1.2114 0.01068 0.00519 -0.0454 0.1904 1.0000
8.250 1.2376 0.01108 0.00547 -0.0455 0.1625 1.0000
8.500 1.2539 0.01323 0.00697 -0.0451 0.0622 1.0000
8.750 1.2750 0.01440 0.00793 -0.0448 0.0297 1.0000
9.000 1.2981 0.01516 0.00863 -0.0446 0.0200 1.0000
9.250 1.3214 0.01584 0.00933 -0.0443 0.0168 1.0000
9.500 1.3453 0.01638 0.00991 -0.0441 0.0157 1.0000
9.750 1.3681 0.01702 0.01060 -0.0438 0.0145 1.0000
10.000 1.3882 0.01798 0.01162 -0.0433 0.0132 1.0000
10.250 1.4101 0.01863 0.01233 -0.0429 0.0127 1.0000
10.500 1.4313 0.01930 0.01306 -0.0425 0.0121 1.0000
10.750 1.4513 0.02005 0.01387 -0.0420 0.0115 1.0000
11.000 1.4696 0.02092 0.01480 -0.0414 0.0109 1.0000
11.250 1.4832 0.02217 0.01612 -0.0404 0.0104 1.0000
11.500 1.4874 0.02405 0.01814 -0.0388 0.0099 1.0000
11.750 1.4961 0.02526 0.01943 -0.0376 0.0098 1.0000
12.000 1.5038 0.02694 0.02119 -0.0372 0.0096 1.0000
12.250 1.5105 0.02894 0.02329 -0.0372 0.0094 1.0000
12.500 1.5159 0.03119 0.02564 -0.0373 0.0092 1.0000
12.750 1.5198 0.03365 0.02819 -0.0376 0.0089 1.0000
13.000 1.5218 0.03636 0.03099 -0.0378 0.0087 1.0000
13.250 1.5223 0.03928 0.03400 -0.0381 0.0086 1.0000
13.500 1.5209 0.04241 0.03721 -0.0384 0.0084 1.0000
13.750 1.5187 0.04564 0.04053 -0.0387 0.0083 1.0000
14.000 1.5143 0.04918 0.04415 -0.0391 0.0081 1.0000
14.250 1.5080 0.05297 0.04804 -0.0396 0.0080 1.0000
14.500 1.4990 0.05717 0.05232 -0.0403 0.0079 1.0000
14.750 1.4874 0.06178 0.05704 -0.0411 0.0078 1.0000
15.000 1.4745 0.06677 0.06213 -0.0421 0.0076 1.0000
15.250 1.4588 0.07226 0.06773 -0.0433 0.0075 1.0000
15.500 1.4458 0.07743 0.07300 -0.0444 0.0074 1.0000
15.750 1.4429 0.08145 0.07712 -0.0455 0.0073 1.0000
16.000 1.4385 0.08569 0.08144 -0.0467 0.0073 1.0000
16.250 1.4338 0.09001 0.08585 -0.0480 0.0072 1.0000
16.500 1.4286 0.09443 0.09036 -0.0493 0.0071 1.0000
16.750 1.4234 0.09889 0.09491 -0.0506 0.0071 1.0000
17.000 1.4180 0.10336 0.09947 -0.0520 0.0070 1.0000
17.250 1.4125 0.10792 0.10412 -0.0535 0.0069 1.0000
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Polar data table (+)
Polar graphs
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