GOE 613 AIRFOIL (goe613-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 613 AIRFOIL (goe613-il) Reynolds number: 200,000 Max Cl/Cd: 67.87 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe613-il-200000-n5.txt Download as CSV file: xf-goe613-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 613 AIRFOIL
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-9.250 -0.3298 0.10109 0.09766 -0.0338 1.0000 0.0237
-9.000 -0.3357 0.09861 0.09523 -0.0331 1.0000 0.0247
-8.750 -0.3433 0.09619 0.09287 -0.0319 1.0000 0.0245
-8.500 -0.3363 0.09191 0.08861 -0.0355 0.9973 0.0243
-8.250 -0.3262 0.08728 0.08398 -0.0403 0.9929 0.0242
-8.000 -0.3169 0.08250 0.07921 -0.0457 0.9874 0.0244
-7.750 -0.3102 0.07761 0.07433 -0.0517 0.9795 0.0248
-7.500 -0.2993 0.06759 0.06422 -0.0670 0.9680 0.0265
-7.250 -0.2856 0.06031 0.05680 -0.0747 0.9612 0.0270
-7.000 -0.2692 0.05874 0.05523 -0.0754 0.9560 0.0278
-6.750 -0.2469 0.05464 0.05101 -0.0797 0.9519 0.0284
-6.500 -0.2288 0.05161 0.04788 -0.0818 0.9447 0.0296
-6.250 -0.2044 0.04709 0.04312 -0.0858 0.9395 0.0316
-6.000 -0.1814 0.04169 0.03739 -0.0891 0.9340 0.0322
-5.750 -0.1612 0.03672 0.03197 -0.0904 0.9266 0.0333
-5.500 -0.1331 0.03241 0.02699 -0.0920 0.9225 0.0350
-5.250 -0.1151 0.02928 0.02354 -0.0915 0.9147 0.0354
-5.000 -0.0885 0.02697 0.02098 -0.0923 0.9098 0.0360
-4.750 -0.0565 0.02568 0.01959 -0.0939 0.9065 0.0372
-4.500 -0.0346 0.02453 0.01827 -0.0930 0.8977 0.0384
-4.250 -0.0042 0.02269 0.01610 -0.0937 0.8927 0.0389
-4.000 0.0201 0.02127 0.01440 -0.0931 0.8851 0.0393
-3.750 0.0487 0.01997 0.01283 -0.0932 0.8794 0.0398
-3.500 0.0767 0.01890 0.01152 -0.0931 0.8733 0.0403
-3.250 0.1034 0.01801 0.01044 -0.0928 0.8659 0.0409
-3.000 0.1329 0.01731 0.00957 -0.0929 0.8594 0.0425
-2.750 0.1602 0.01661 0.00870 -0.0926 0.8495 0.0433
-2.500 0.1869 0.01590 0.00786 -0.0921 0.8375 0.0436
-2.250 0.2143 0.01527 0.00712 -0.0917 0.8252 0.0440
-2.000 0.2419 0.01472 0.00647 -0.0914 0.8141 0.0445
-1.750 0.2696 0.01426 0.00593 -0.0912 0.8035 0.0451
-1.500 0.2948 0.01367 0.00531 -0.0905 0.7915 0.0459
-1.250 0.3204 0.01318 0.00480 -0.0899 0.7793 0.0472
-1.000 0.3463 0.01284 0.00443 -0.0894 0.7664 0.0486
-0.750 0.3725 0.01260 0.00414 -0.0889 0.7529 0.0509
-0.500 0.3984 0.01242 0.00388 -0.0884 0.7384 0.0538
-0.250 0.4240 0.01227 0.00364 -0.0878 0.7235 0.0559
0.000 0.4492 0.01214 0.00342 -0.0871 0.7073 0.0580
0.250 0.4738 0.01201 0.00322 -0.0862 0.6899 0.0628
0.500 0.4983 0.01195 0.00309 -0.0854 0.6711 0.0700
0.750 0.5214 0.01175 0.00302 -0.0844 0.6507 0.1265
1.000 0.6074 0.00983 0.00322 -0.0970 0.6150 1.0000
1.250 0.6272 0.01002 0.00319 -0.0952 0.5865 1.0000
1.500 0.6463 0.01025 0.00320 -0.0933 0.5600 1.0000
1.750 0.6660 0.01049 0.00325 -0.0916 0.5383 1.0000
2.000 0.6861 0.01074 0.00333 -0.0900 0.5199 1.0000
2.250 0.7065 0.01098 0.00344 -0.0885 0.5029 1.0000
2.500 0.7272 0.01122 0.00356 -0.0870 0.4862 1.0000
2.750 0.7480 0.01146 0.00369 -0.0856 0.4694 1.0000
3.000 0.7690 0.01169 0.00384 -0.0842 0.4532 1.0000
3.250 0.7900 0.01193 0.00399 -0.0829 0.4374 1.0000
3.500 0.8110 0.01217 0.00416 -0.0816 0.4223 1.0000
3.750 0.8320 0.01243 0.00434 -0.0802 0.4077 1.0000
4.000 0.8529 0.01269 0.00453 -0.0789 0.3934 1.0000
4.250 0.8736 0.01297 0.00474 -0.0776 0.3800 1.0000
4.750 0.9156 0.01354 0.00521 -0.0750 0.3567 1.0000
5.000 0.9368 0.01382 0.00547 -0.0738 0.3475 1.0000
5.250 0.9577 0.01414 0.00575 -0.0726 0.3388 1.0000
5.500 0.9793 0.01443 0.00605 -0.0715 0.3301 1.0000
5.750 0.9999 0.01477 0.00635 -0.0702 0.3224 1.0000
6.000 1.0213 0.01506 0.00667 -0.0691 0.3134 1.0000
6.250 1.0414 0.01540 0.00700 -0.0678 0.3028 1.0000
6.500 1.0601 0.01575 0.00731 -0.0662 0.2878 1.0000
6.750 1.0788 0.01611 0.00763 -0.0647 0.2737 1.0000
7.000 1.0973 0.01648 0.00797 -0.0632 0.2610 1.0000
7.250 1.1160 0.01684 0.00832 -0.0617 0.2489 1.0000
7.500 1.1349 0.01718 0.00871 -0.0602 0.2373 1.0000
7.750 1.1517 0.01758 0.00909 -0.0584 0.2231 1.0000
8.000 1.1673 0.01802 0.00950 -0.0564 0.2068 1.0000
8.250 1.1810 0.01859 0.00997 -0.0542 0.1813 1.0000
8.500 1.1891 0.01953 0.01064 -0.0513 0.1381 1.0000
8.750 1.1915 0.02096 0.01172 -0.0477 0.0898 1.0000
9.000 1.1816 0.02325 0.01352 -0.0427 0.0237 1.0000
9.250 1.1920 0.02417 0.01449 -0.0403 0.0202 1.0000
9.500 1.2036 0.02503 0.01547 -0.0382 0.0188 1.0000
9.750 1.2140 0.02597 0.01655 -0.0361 0.0177 1.0000
10.000 1.2220 0.02710 0.01781 -0.0338 0.0164 1.0000
10.250 1.2280 0.02839 0.01925 -0.0314 0.0154 1.0000
10.500 1.2321 0.02986 0.02088 -0.0290 0.0147 1.0000
10.750 1.2365 0.03133 0.02253 -0.0269 0.0142 1.0000
11.000 1.2410 0.03286 0.02420 -0.0249 0.0139 1.0000
11.250 1.2436 0.03459 0.02608 -0.0230 0.0136 1.0000
11.500 1.2443 0.03656 0.02820 -0.0213 0.0134 1.0000
11.750 1.2428 0.03882 0.03061 -0.0197 0.0131 1.0000
12.000 1.2406 0.04130 0.03323 -0.0185 0.0128 1.0000
12.250 1.2371 0.04405 0.03611 -0.0175 0.0124 1.0000
12.500 1.2329 0.04703 0.03921 -0.0169 0.0121 1.0000
12.750 1.2278 0.05027 0.04257 -0.0166 0.0117 1.0000
13.000 1.2207 0.05393 0.04636 -0.0166 0.0114 1.0000
13.250 1.2150 0.05764 0.05018 -0.0169 0.0113 1.0000
13.500 1.2065 0.06185 0.05451 -0.0176 0.0110 1.0000
13.750 1.2004 0.06589 0.05864 -0.0183 0.0108 1.0000
14.000 1.1943 0.06997 0.06280 -0.0190 0.0107 1.0000
14.250 1.1885 0.07390 0.06678 -0.0195 0.0105 1.0000
14.500 1.1865 0.07716 0.07006 -0.0195 0.0103 1.0000
14.750 1.1875 0.08036 0.07334 -0.0200 0.0102 1.0000
15.000 1.1889 0.08354 0.07663 -0.0205 0.0101 1.0000
15.250 1.1912 0.08654 0.07971 -0.0209 0.0100 1.0000
15.500 1.1927 0.08978 0.08308 -0.0215 0.0098 1.0000
15.750 1.1957 0.09272 0.08612 -0.0219 0.0097 1.0000
16.000 1.1981 0.09584 0.08935 -0.0225 0.0096 1.0000
16.250 1.2003 0.09902 0.09264 -0.0231 0.0095 1.0000
16.500 1.2008 0.10258 0.09634 -0.0241 0.0093 1.0000
16.750 1.2003 0.10639 0.10030 -0.0254 0.0091 1.0000
17.000 1.1992 0.11036 0.10441 -0.0269 0.0089 1.0000
17.250 1.1973 0.11454 0.10872 -0.0286 0.0087 1.0000
17.500 1.1954 0.11874 0.11306 -0.0304 0.0086 1.0000
17.750 1.1929 0.12310 0.11753 -0.0326 0.0083 1.0000
18.000 1.1897 0.12766 0.12223 -0.0347 0.0082 1.0000
18.250 1.1874 0.13206 0.12674 -0.0370 0.0081 1.0000
18.500 1.1828 0.13711 0.13193 -0.0397 0.0080 1.0000
18.750 1.1784 0.14214 0.13710 -0.0425 0.0080 1.0000
19.000 1.1738 0.14726 0.14235 -0.0454 0.0079 1.0000
19.250 1.1676 0.15291 0.14815 -0.0488 0.0079 1.0000
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