GOE 512 AIRFOIL (goe512-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 512 AIRFOIL (goe512-il) Reynolds number: 1,000,000 Max Cl/Cd: 95.86 at α=8.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe512-il-1000000.txt Download as CSV file: xf-goe512-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 512 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
------ -------- --------- --------- -------- -------- --------
-14.000 -0.6951 0.06222 0.05997 -0.0842 0.9933 0.0125
-13.750 -0.8165 0.03877 0.03607 -0.1056 0.9842 0.0121
-13.500 -0.8168 0.03369 0.03073 -0.1072 0.9810 0.0123
-13.250 -0.8140 0.03100 0.02784 -0.1059 0.9763 0.0123
-13.000 -0.7995 0.02865 0.02529 -0.1062 0.9739 0.0125
-12.750 -0.7778 0.02704 0.02351 -0.1068 0.9724 0.0126
-12.500 -0.7522 0.02582 0.02216 -0.1076 0.9715 0.0128
-12.250 -0.7482 0.02415 0.02030 -0.1045 0.9666 0.0131
-12.000 -0.7356 0.02267 0.01869 -0.1027 0.9628 0.0135
-11.750 -0.7124 0.02159 0.01752 -0.1026 0.9610 0.0137
-11.500 -0.6840 0.02082 0.01669 -0.1033 0.9598 0.0141
-11.250 -0.6553 0.01988 0.01566 -0.1040 0.9589 0.0143
-11.000 -0.6228 0.01908 0.01477 -0.1053 0.9581 0.0148
-10.750 -0.5900 0.01823 0.01382 -0.1067 0.9574 0.0152
-10.500 -0.5745 0.01769 0.01319 -0.1043 0.9526 0.0155
-10.250 -0.5513 0.01701 0.01241 -0.1035 0.9492 0.0157
-10.000 -0.5249 0.01608 0.01137 -0.1035 0.9472 0.0162
-9.750 -0.4943 0.01532 0.01057 -0.1043 0.9459 0.0169
-9.500 -0.4585 0.01483 0.01004 -0.1061 0.9449 0.0176
-9.250 -0.4226 0.01426 0.00941 -0.1078 0.9436 0.0182
-9.000 -0.3877 0.01377 0.00885 -0.1093 0.9421 0.0188
-8.750 -0.3758 0.01352 0.00854 -0.1058 0.9353 0.0192
-8.500 -0.3497 0.01281 0.00779 -0.1055 0.9316 0.0202
-8.250 -0.3163 0.01247 0.00743 -0.1066 0.9289 0.0213
-8.000 -0.2821 0.01212 0.00703 -0.1079 0.9259 0.0223
-7.750 -0.2664 0.01192 0.00678 -0.1050 0.9176 0.0229
-7.500 -0.2365 0.01132 0.00615 -0.1054 0.9128 0.0242
-7.250 -0.2147 0.01110 0.00590 -0.1040 0.9049 0.0252
-7.000 -0.1844 0.01085 0.00560 -0.1043 0.8980 0.0265
-6.750 -0.1601 0.01054 0.00524 -0.1034 0.8888 0.0277
-6.500 -0.1295 0.01022 0.00489 -0.1039 0.8806 0.0294
-6.250 -0.1043 0.01009 0.00472 -0.1031 0.8688 0.0310
-6.000 -0.0771 0.00994 0.00449 -0.1027 0.8565 0.0322
-5.750 -0.0521 0.00963 0.00413 -0.1020 0.8434 0.0342
-5.500 -0.0266 0.00953 0.00397 -0.1013 0.8298 0.0360
-5.250 -0.0022 0.00948 0.00383 -0.1004 0.8156 0.0375
-5.000 0.0198 0.00927 0.00355 -0.0989 0.8005 0.0397
-4.750 0.0416 0.00919 0.00342 -0.0974 0.7844 0.0416
-4.500 0.0622 0.00916 0.00331 -0.0956 0.7644 0.0434
-4.250 0.0814 0.00909 0.00314 -0.0936 0.7425 0.0456
-4.000 0.0985 0.00905 0.00300 -0.0911 0.7176 0.0480
-3.750 0.1165 0.00907 0.00292 -0.0887 0.6930 0.0503
-3.500 0.1343 0.00913 0.00286 -0.0864 0.6707 0.0521
-3.250 0.1532 0.00902 0.00269 -0.0843 0.6539 0.0563
-3.000 0.1741 0.00900 0.00262 -0.0826 0.6404 0.0596
-2.750 0.1949 0.00897 0.00252 -0.0810 0.6274 0.0635
-2.500 0.2149 0.00891 0.00243 -0.0791 0.6146 0.0689
-2.250 0.2353 0.00890 0.00235 -0.0774 0.6022 0.0734
-2.000 0.2559 0.00879 0.00225 -0.0757 0.5900 0.0833
-1.750 0.2736 0.00863 0.00216 -0.0734 0.5769 0.1137
-1.500 0.2882 0.00844 0.00209 -0.0705 0.5631 0.1637
-1.250 0.3036 0.00835 0.00212 -0.0678 0.5477 0.2125
-1.000 0.3227 0.00843 0.00215 -0.0658 0.5309 0.2327
-0.750 0.3411 0.00854 0.00219 -0.0636 0.5087 0.2423
-0.500 0.3607 0.00868 0.00224 -0.0617 0.4896 0.2497
-0.250 0.3797 0.00881 0.00228 -0.0598 0.4716 0.2553
0.000 0.4005 0.00894 0.00236 -0.0582 0.4588 0.2613
0.250 0.4215 0.00907 0.00242 -0.0566 0.4481 0.2651
0.500 0.4431 0.00920 0.00248 -0.0552 0.4391 0.2682
0.750 0.4640 0.00926 0.00252 -0.0537 0.4318 0.2730
1.000 0.4862 0.00934 0.00258 -0.0524 0.4250 0.2762
1.250 0.5072 0.00946 0.00265 -0.0510 0.4181 0.2789
1.500 0.5306 0.00953 0.00270 -0.0499 0.4132 0.2815
1.750 0.5530 0.00964 0.00277 -0.0488 0.4076 0.2834
2.000 0.5726 0.00969 0.00282 -0.0470 0.4021 0.2883
2.250 0.5954 0.00975 0.00288 -0.0459 0.3975 0.2917
2.500 0.6175 0.00981 0.00294 -0.0447 0.3924 0.2940
2.750 0.6385 0.00992 0.00301 -0.0433 0.3869 0.2953
3.000 0.6607 0.00999 0.00307 -0.0421 0.3822 0.2968
3.250 0.6833 0.01006 0.00314 -0.0411 0.3767 0.2982
3.500 0.7039 0.01015 0.00320 -0.0396 0.3707 0.3004
3.750 0.7249 0.01022 0.00327 -0.0382 0.3649 0.3030
4.000 0.7461 0.01029 0.00335 -0.0369 0.3583 0.3059
4.250 0.7662 0.01042 0.00345 -0.0354 0.3511 0.3076
4.500 0.7882 0.01050 0.00353 -0.0343 0.3441 0.3098
4.750 0.8080 0.01066 0.00364 -0.0328 0.3352 0.3119
5.000 0.8292 0.01078 0.00375 -0.0315 0.3261 0.3135
5.250 0.8481 0.01094 0.00388 -0.0298 0.3154 0.3163
5.500 0.8661 0.01114 0.00404 -0.0280 0.3033 0.3190
5.750 0.8844 0.01135 0.00420 -0.0263 0.2912 0.3220
6.000 0.9025 0.01157 0.00439 -0.0246 0.2798 0.3251
6.250 0.9202 0.01182 0.00460 -0.0228 0.2701 0.3291
6.500 0.9374 0.01205 0.00482 -0.0209 0.2618 0.3355
6.750 0.9548 0.01227 0.00504 -0.0191 0.2548 0.3446
7.000 1.1104 0.01191 0.00615 -0.0485 0.2410 0.9850
7.250 1.1501 0.01225 0.00649 -0.0515 0.2376 0.9903
7.500 1.1898 0.01264 0.00686 -0.0546 0.2340 0.9947
7.750 1.2326 0.01305 0.00723 -0.0585 0.2291 0.9976
8.000 1.2752 0.01335 0.00754 -0.0622 0.2260 0.9995
8.250 1.2999 0.01356 0.00776 -0.0620 0.2231 1.0000
8.500 1.3143 0.01379 0.00801 -0.0597 0.2201 1.0000
8.750 1.3276 0.01407 0.00829 -0.0572 0.2175 1.0000
9.000 1.3392 0.01442 0.00863 -0.0545 0.2142 1.0000
9.250 1.3517 0.01476 0.00899 -0.0519 0.2117 1.0000
9.500 1.3683 0.01497 0.00924 -0.0501 0.2104 1.0000
9.750 1.3842 0.01521 0.00952 -0.0482 0.2086 1.0000
10.000 1.3996 0.01549 0.00982 -0.0463 0.2062 1.0000
10.250 1.4140 0.01582 0.01017 -0.0443 0.2037 1.0000
10.500 1.4264 0.01625 0.01060 -0.0419 0.2001 1.0000
10.750 1.4381 0.01673 0.01109 -0.0396 0.1969 1.0000
11.000 1.4556 0.01698 0.01139 -0.0381 0.1952 1.0000
11.250 1.4720 0.01729 0.01174 -0.0366 0.1919 1.0000
11.500 1.4862 0.01771 0.01217 -0.0348 0.1880 1.0000
11.750 1.4978 0.01827 0.01273 -0.0326 0.1838 1.0000
12.000 1.5134 0.01867 0.01316 -0.0311 0.1800 1.0000
12.250 1.5270 0.01918 0.01367 -0.0294 0.1732 1.0000
12.500 1.5381 0.01983 0.01431 -0.0274 0.1650 1.0000
12.750 1.5453 0.02073 0.01514 -0.0250 0.1515 1.0000
13.000 1.5421 0.02224 0.01650 -0.0216 0.1306 1.0000
13.250 1.5392 0.02383 0.01801 -0.0184 0.1153 1.0000
13.500 1.5345 0.02564 0.01976 -0.0152 0.1009 1.0000
13.750 1.5205 0.02821 0.02220 -0.0116 0.0800 1.0000
14.000 1.4974 0.03170 0.02554 -0.0078 0.0551 1.0000
14.250 1.4674 0.03615 0.02989 -0.0044 0.0301 1.0000
14.500 1.4508 0.03985 0.03359 -0.0025 0.0193 1.0000
14.750 1.4463 0.04261 0.03641 -0.0014 0.0169 1.0000
15.000 1.4453 0.04514 0.03902 -0.0007 0.0160 1.0000
15.250 1.4411 0.04808 0.04204 -0.0001 0.0149 1.0000
15.500 1.4370 0.05109 0.04513 0.0004 0.0144 1.0000
15.750 1.4286 0.05469 0.04883 0.0007 0.0136 1.0000
16.000 1.4252 0.05780 0.05203 0.0008 0.0134 1.0000
16.250 1.4197 0.06125 0.05557 0.0008 0.0129 1.0000
16.500 1.4134 0.06486 0.05927 0.0006 0.0127 1.0000
16.750 1.4049 0.06885 0.06336 0.0002 0.0124 1.0000
17.000 1.3946 0.07318 0.06779 -0.0004 0.0121 1.0000
17.250 1.3828 0.07779 0.07251 -0.0011 0.0119 1.0000
17.500 1.3686 0.08279 0.07761 -0.0020 0.0115 1.0000
17.750 1.3521 0.08821 0.08314 -0.0031 0.0113 1.0000
18.000 1.3386 0.09329 0.08833 -0.0043 0.0112 1.0000
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Polar data table (+)
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