GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 323 (HANSA-BRANDENBURG V.1) AIRFOIL (goe323-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.09 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe323-il-1000000-n5.txt Download as CSV file: xf-goe323-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 323 (HANSA-BRANDENBURG V.1) 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
------ -------- --------- --------- -------- -------- --------
-10.250 -0.4026 0.11419 0.11115 0.0083 0.5858 0.0136
-10.000 -0.3974 0.11072 0.10767 0.0067 0.5829 0.0139
-9.750 -0.4074 0.10304 0.09998 0.0027 0.5814 0.0150
-9.250 -0.3911 0.09791 0.09484 0.0001 0.5755 0.0153
-9.000 -0.3825 0.09544 0.09237 -0.0012 0.5724 0.0154
-8.750 -0.3740 0.09287 0.08980 -0.0027 0.5693 0.0155
-8.500 -0.3662 0.09011 0.08704 -0.0044 0.5663 0.0157
-8.250 -0.3596 0.08700 0.08392 -0.0064 0.5636 0.0159
-7.750 -0.3485 0.08001 0.07694 -0.0124 0.5590 0.0164
-7.500 -0.3382 0.07553 0.07245 -0.0180 0.5569 0.0167
-7.250 -0.3320 0.06460 0.06144 -0.0316 0.5556 0.0180
-7.000 -0.3137 0.06116 0.05795 -0.0354 0.5530 0.0181
-6.750 -0.2938 0.05811 0.05485 -0.0386 0.5503 0.0183
-6.500 -0.2730 0.05510 0.05177 -0.0415 0.5477 0.0184
-6.250 -0.2512 0.05190 0.04849 -0.0444 0.5451 0.0186
-6.000 -0.2285 0.04848 0.04497 -0.0472 0.5428 0.0188
-5.750 -0.2050 0.04477 0.04116 -0.0499 0.5408 0.0191
-5.500 -0.1923 0.02296 0.01818 -0.0571 0.5404 0.0214
-5.250 -0.1662 0.02177 0.01686 -0.0572 0.5377 0.0216
-5.000 -0.1398 0.02067 0.01563 -0.0572 0.5350 0.0218
-4.750 -0.1145 0.01860 0.01329 -0.0571 0.5325 0.0221
-4.500 -0.0897 0.01595 0.01025 -0.0570 0.5303 0.0227
-4.250 -0.0634 0.01434 0.00835 -0.0568 0.5279 0.0232
-4.000 -0.0361 0.01334 0.00717 -0.0566 0.5258 0.0235
-3.750 -0.0083 0.01262 0.00631 -0.0565 0.5231 0.0238
-3.500 0.0196 0.01206 0.00564 -0.0563 0.5193 0.0240
-3.250 0.0477 0.01161 0.00509 -0.0562 0.5154 0.0243
-3.000 0.0758 0.01126 0.00465 -0.0561 0.5117 0.0245
-2.750 0.1041 0.01095 0.00427 -0.0560 0.5084 0.0246
-2.500 0.1324 0.01061 0.00389 -0.0559 0.5047 0.0249
-2.250 0.1606 0.01027 0.00351 -0.0558 0.5009 0.0254
-2.000 0.1890 0.01008 0.00330 -0.0557 0.4972 0.0257
-1.750 0.2174 0.00991 0.00310 -0.0556 0.4941 0.0260
-1.500 0.2460 0.00974 0.00292 -0.0556 0.4916 0.0263
-1.250 0.2746 0.00958 0.00275 -0.0555 0.4886 0.0266
-1.000 0.3031 0.00942 0.00258 -0.0555 0.4852 0.0270
-0.750 0.3317 0.00929 0.00243 -0.0554 0.4817 0.0274
-0.500 0.3601 0.00917 0.00228 -0.0554 0.4778 0.0278
-0.250 0.3888 0.00905 0.00215 -0.0554 0.4747 0.0282
0.000 0.4175 0.00895 0.00205 -0.0553 0.4706 0.0286
0.250 0.4461 0.00888 0.00196 -0.0553 0.4657 0.0289
0.500 0.4745 0.00877 0.00183 -0.0553 0.4607 0.0297
0.750 0.5032 0.00870 0.00178 -0.0553 0.4540 0.0305
1.000 0.5317 0.00870 0.00175 -0.0553 0.4459 0.0314
1.250 0.5603 0.00866 0.00171 -0.0553 0.4388 0.0324
1.500 0.5888 0.00866 0.00168 -0.0553 0.4307 0.0332
1.750 0.6173 0.00865 0.00166 -0.0553 0.4208 0.0341
2.000 0.6456 0.00869 0.00167 -0.0553 0.4069 0.0357
2.250 0.6736 0.00878 0.00170 -0.0553 0.3901 0.0375
2.500 0.7015 0.00890 0.00176 -0.0553 0.3727 0.0396
2.750 0.7292 0.00905 0.00185 -0.0553 0.3549 0.0434
3.000 0.7567 0.00924 0.00197 -0.0553 0.3365 0.0479
3.250 0.7842 0.00942 0.00209 -0.0553 0.3203 0.0535
3.500 0.8120 0.00954 0.00220 -0.0553 0.3087 0.0676
3.750 0.8302 0.00796 0.00251 -0.0540 0.3010 0.8772
4.250 0.8958 0.00815 0.00276 -0.0560 0.2827 1.0000
4.500 0.9231 0.00834 0.00289 -0.0560 0.2749 1.0000
4.750 0.9506 0.00851 0.00302 -0.0559 0.2687 1.0000
5.000 0.9778 0.00871 0.00317 -0.0558 0.2603 1.0000
5.250 1.0050 0.00891 0.00333 -0.0558 0.2525 1.0000
5.500 1.0321 0.00911 0.00349 -0.0557 0.2452 1.0000
5.750 1.0592 0.00932 0.00366 -0.0557 0.2388 1.0000
6.000 1.0862 0.00953 0.00384 -0.0556 0.2314 1.0000
6.250 1.1129 0.00977 0.00404 -0.0556 0.2242 1.0000
6.500 1.1398 0.00999 0.00423 -0.0555 0.2177 1.0000
7.000 1.1930 0.01046 0.00466 -0.0554 0.2057 1.0000
7.250 1.2193 0.01073 0.00490 -0.0553 0.1991 1.0000
7.500 1.2456 0.01098 0.00514 -0.0553 0.1942 1.0000
7.750 1.2718 0.01124 0.00538 -0.0552 0.1879 1.0000
8.000 1.2972 0.01158 0.00568 -0.0551 0.1803 1.0000
8.250 1.3229 0.01188 0.00596 -0.0549 0.1735 1.0000
8.500 1.3477 0.01226 0.00630 -0.0548 0.1652 1.0000
8.750 1.3727 0.01259 0.00661 -0.0546 0.1584 1.0000
9.000 1.3972 0.01297 0.00697 -0.0544 0.1521 1.0000
9.250 1.4219 0.01332 0.00731 -0.0542 0.1455 1.0000
9.500 1.4452 0.01379 0.00773 -0.0539 0.1362 1.0000
9.750 1.4674 0.01434 0.00822 -0.0535 0.1246 1.0000
10.000 1.4875 0.01507 0.00885 -0.0529 0.1074 1.0000
10.250 1.5045 0.01604 0.00969 -0.0520 0.0896 1.0000
10.500 1.5237 0.01676 0.01037 -0.0513 0.0825 1.0000
10.750 1.5441 0.01733 0.01095 -0.0507 0.0780 1.0000
11.000 1.5631 0.01797 0.01161 -0.0501 0.0739 1.0000
11.250 1.5804 0.01872 0.01235 -0.0492 0.0695 1.0000
11.500 1.5976 0.01940 0.01305 -0.0484 0.0650 1.0000
11.750 1.5988 0.02100 0.01457 -0.0461 0.0496 1.0000
12.000 1.5797 0.02504 0.01848 -0.0449 0.0220 1.0000
12.250 1.5822 0.02770 0.02117 -0.0453 0.0166 1.0000
12.500 1.5894 0.02981 0.02334 -0.0455 0.0150 1.0000
12.750 1.5949 0.03202 0.02561 -0.0455 0.0139 1.0000
13.000 1.6000 0.03423 0.02787 -0.0454 0.0131 1.0000
13.250 1.6049 0.03641 0.03011 -0.0453 0.0126 1.0000
13.500 1.6081 0.03875 0.03252 -0.0452 0.0121 1.0000
13.750 1.6097 0.04123 0.03507 -0.0450 0.0117 1.0000
14.000 1.6101 0.04387 0.03777 -0.0448 0.0113 1.0000
14.250 1.6088 0.04667 0.04063 -0.0447 0.0109 1.0000
14.500 1.6066 0.04959 0.04363 -0.0445 0.0105 1.0000
14.750 1.6057 0.05241 0.04652 -0.0445 0.0103 1.0000
15.000 1.6043 0.05534 0.04953 -0.0445 0.0101 1.0000
15.250 1.6034 0.05837 0.05263 -0.0447 0.0098 1.0000
15.500 1.6017 0.06156 0.05590 -0.0450 0.0096 1.0000
15.750 1.5986 0.06498 0.05939 -0.0453 0.0093 1.0000
16.000 1.5951 0.06852 0.06301 -0.0458 0.0091 1.0000
16.250 1.5909 0.07218 0.06675 -0.0463 0.0089 1.0000
16.500 1.5849 0.07614 0.07078 -0.0470 0.0087 1.0000
16.750 1.5776 0.08036 0.07509 -0.0478 0.0085 1.0000
17.000 1.5693 0.08480 0.07962 -0.0487 0.0083 1.0000
17.250 1.5602 0.08938 0.08430 -0.0497 0.0082 1.0000
17.500 1.5530 0.09378 0.08878 -0.0507 0.0081 1.0000
17.750 1.5450 0.09835 0.09345 -0.0519 0.0080 1.0000
18.000 1.5362 0.10311 0.09831 -0.0532 0.0079 1.0000
18.250 1.5263 0.10807 0.10336 -0.0547 0.0078 1.0000
18.500 1.5160 0.11317 0.10856 -0.0563 0.0077 1.0000
18.750 1.5054 0.11840 0.11389 -0.0581 0.0076 1.0000
19.000 1.4945 0.12372 0.11930 -0.0600 0.0075 1.0000
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