GOE 504 AIRFOIL (goe504-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 504 AIRFOIL (goe504-il) Reynolds number: 1,000,000 Max Cl/Cd: 114.89 at α=4.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe504-il-1000000.txt Download as CSV file: xf-goe504-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 504 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
------ -------- --------- --------- -------- -------- --------
-16.250 -0.6202 0.08142 0.07912 -0.0855 0.9984 0.0135
-16.000 -0.6380 0.07345 0.07102 -0.0921 0.9972 0.0136
-15.750 -0.6461 0.06720 0.06467 -0.0980 0.9957 0.0137
-15.500 -0.6633 0.05960 0.05691 -0.1050 0.9939 0.0137
-15.250 -0.6683 0.05418 0.05139 -0.1101 0.9914 0.0138
-15.000 -0.6586 0.05045 0.04760 -0.1147 0.9889 0.0140
-14.750 -0.6675 0.04382 0.04078 -0.1218 0.9861 0.0140
-14.500 -0.6514 0.04047 0.03734 -0.1272 0.9841 0.0142
-14.250 -0.6413 0.03670 0.03345 -0.1325 0.9812 0.0145
-14.000 -0.6358 0.03307 0.02968 -0.1367 0.9757 0.0146
-13.750 -0.6167 0.03082 0.02733 -0.1407 0.9721 0.0150
-13.500 -0.5995 0.02830 0.02465 -0.1447 0.9681 0.0153
-13.250 -0.5772 0.02693 0.02316 -0.1474 0.9615 0.0157
-13.000 -0.5491 0.02504 0.02111 -0.1516 0.9576 0.0158
-12.750 -0.5314 0.02306 0.01898 -0.1539 0.9487 0.0164
-12.500 -0.5004 0.02233 0.01822 -0.1565 0.9412 0.0167
-12.250 -0.4819 0.02175 0.01756 -0.1563 0.9289 0.0170
-12.000 -0.4671 0.02111 0.01682 -0.1552 0.9150 0.0173
-11.750 -0.4549 0.02059 0.01619 -0.1533 0.8997 0.0175
-11.500 -0.4450 0.02021 0.01570 -0.1507 0.8837 0.0179
-11.250 -0.4374 0.01966 0.01502 -0.1476 0.8674 0.0182
-11.000 -0.4290 0.01926 0.01449 -0.1445 0.8519 0.0185
-10.750 -0.4160 0.01890 0.01400 -0.1421 0.8379 0.0189
-10.500 -0.4019 0.01858 0.01354 -0.1399 0.8248 0.0192
-10.250 -0.3863 0.01838 0.01320 -0.1379 0.8127 0.0195
-10.000 -0.3765 0.01714 0.01186 -0.1353 0.8010 0.0201
-9.750 -0.3592 0.01680 0.01148 -0.1337 0.7906 0.0205
-9.500 -0.3415 0.01646 0.01107 -0.1321 0.7809 0.0209
-9.250 -0.3220 0.01625 0.01079 -0.1307 0.7717 0.0214
-9.000 -0.3026 0.01592 0.01038 -0.1293 0.7634 0.0219
-8.750 -0.2833 0.01554 0.00992 -0.1279 0.7548 0.0224
-8.500 -0.2627 0.01522 0.00953 -0.1266 0.7472 0.0229
-8.250 -0.2415 0.01495 0.00918 -0.1255 0.7397 0.0233
-8.000 -0.2184 0.01492 0.00906 -0.1246 0.7327 0.0237
-7.750 -0.2043 0.01383 0.00793 -0.1224 0.7254 0.0245
-7.500 -0.1845 0.01345 0.00751 -0.1211 0.7186 0.0252
-7.250 -0.1627 0.01312 0.00715 -0.1201 0.7122 0.0257
-7.000 -0.1414 0.01283 0.00680 -0.1189 0.7054 0.0263
-6.750 -0.1193 0.01253 0.00647 -0.1179 0.6992 0.0269
-6.500 -0.0968 0.01228 0.00616 -0.1169 0.6927 0.0276
-6.250 -0.0736 0.01211 0.00593 -0.1160 0.6865 0.0282
-6.000 -0.0493 0.01193 0.00571 -0.1153 0.6804 0.0286
-5.750 -0.0296 0.01151 0.00521 -0.1138 0.6739 0.0291
-5.500 -0.0093 0.01107 0.00472 -0.1124 0.6681 0.0299
-5.250 0.0132 0.01078 0.00439 -0.1114 0.6617 0.0306
-5.000 0.0360 0.01060 0.00414 -0.1104 0.6554 0.0315
-4.750 0.0603 0.01039 0.00391 -0.1098 0.6493 0.0323
-4.500 0.0839 0.01023 0.00370 -0.1089 0.6429 0.0330
-4.250 0.1081 0.01009 0.00350 -0.1082 0.6369 0.0337
-4.000 0.1326 0.00995 0.00333 -0.1075 0.6302 0.0342
-3.750 0.1559 0.00984 0.00314 -0.1066 0.6237 0.0350
-3.500 0.1807 0.00967 0.00295 -0.1059 0.6177 0.0367
-3.250 0.2044 0.00956 0.00280 -0.1051 0.6109 0.0384
-3.000 0.2289 0.00947 0.00268 -0.1044 0.6047 0.0402
-2.750 0.2532 0.00938 0.00257 -0.1037 0.5979 0.0456
-2.500 0.2737 0.00908 0.00243 -0.1023 0.5916 0.0955
-2.250 0.2923 0.00855 0.00226 -0.1007 0.5856 0.1975
-2.000 0.3147 0.00844 0.00224 -0.0997 0.5792 0.2352
-1.750 0.3389 0.00840 0.00224 -0.0990 0.5732 0.2546
-1.500 0.3632 0.00838 0.00223 -0.0983 0.5669 0.2701
-1.250 0.3862 0.00840 0.00223 -0.0974 0.5606 0.2810
-1.000 0.4115 0.00838 0.00222 -0.0969 0.5550 0.2911
-0.750 0.4349 0.00838 0.00223 -0.0960 0.5488 0.3028
-0.500 0.4582 0.00840 0.00224 -0.0951 0.5432 0.3129
0.000 0.5047 0.00841 0.00226 -0.0934 0.5317 0.3362
0.250 0.5274 0.00840 0.00227 -0.0924 0.5263 0.3494
0.500 0.5492 0.00838 0.00229 -0.0912 0.5208 0.3681
0.750 0.5682 0.00836 0.00231 -0.0894 0.5151 0.3943
1.000 0.5880 0.00826 0.00235 -0.0879 0.5102 0.4407
1.250 0.6064 0.00811 0.00240 -0.0861 0.5050 0.5099
1.500 0.6204 0.00795 0.00248 -0.0834 0.4993 0.6039
1.750 0.6345 0.00777 0.00259 -0.0806 0.4946 0.7011
2.000 0.6468 0.00758 0.00270 -0.0773 0.4897 0.8006
2.250 0.6724 0.00750 0.00290 -0.0768 0.4836 0.9051
2.500 0.7624 0.00775 0.00316 -0.0906 0.4759 0.9539
2.750 0.8135 0.00798 0.00334 -0.0960 0.4691 0.9675
3.000 0.8541 0.00818 0.00350 -0.0989 0.4634 0.9774
3.250 0.8899 0.00835 0.00364 -0.1009 0.4570 0.9849
3.500 0.9254 0.00857 0.00380 -0.1029 0.4504 0.9904
3.750 0.9617 0.00871 0.00393 -0.1050 0.4450 0.9947
4.000 1.0007 0.00889 0.00407 -0.1077 0.4385 0.9980
4.250 1.0404 0.00907 0.00421 -0.1107 0.4325 1.0000
4.500 1.0501 0.00914 0.00428 -0.1071 0.4273 1.0000
4.750 1.0592 0.00928 0.00438 -0.1035 0.4218 1.0000
5.000 1.0723 0.00941 0.00450 -0.1007 0.4164 1.0000
5.250 1.0870 0.00954 0.00462 -0.0983 0.4107 1.0000
5.500 1.0995 0.00975 0.00479 -0.0955 0.4048 1.0000
5.750 1.1168 0.00989 0.00493 -0.0936 0.3998 1.0000
6.000 1.1327 0.01009 0.00511 -0.0916 0.3932 1.0000
6.250 1.1480 0.01033 0.00533 -0.0894 0.3869 1.0000
6.500 1.1651 0.01055 0.00553 -0.0877 0.3792 1.0000
6.750 1.1804 0.01085 0.00579 -0.0856 0.3708 1.0000
7.000 1.1978 0.01111 0.00604 -0.0841 0.3640 1.0000
7.250 1.2132 0.01145 0.00634 -0.0821 0.3550 1.0000
7.500 1.2292 0.01180 0.00667 -0.0804 0.3464 1.0000
7.750 1.2458 0.01214 0.00699 -0.0788 0.3392 1.0000
8.000 1.2620 0.01253 0.00735 -0.0772 0.3313 1.0000
8.250 1.2777 0.01294 0.00775 -0.0756 0.3231 1.0000
8.750 1.3077 0.01390 0.00865 -0.0723 0.3052 1.0000
9.000 1.3210 0.01449 0.00920 -0.0705 0.2956 1.0000
9.250 1.3329 0.01516 0.00982 -0.0685 0.2840 1.0000
9.500 1.3453 0.01584 0.01047 -0.0668 0.2720 1.0000
9.750 1.3558 0.01664 0.01122 -0.0648 0.2591 1.0000
10.000 1.3645 0.01758 0.01209 -0.0628 0.2451 1.0000
10.250 1.3653 0.01899 0.01336 -0.0599 0.2235 1.0000
10.500 1.3607 0.02079 0.01501 -0.0566 0.1967 1.0000
10.750 1.3499 0.02311 0.01713 -0.0530 0.1638 1.0000
11.000 1.3277 0.02639 0.02016 -0.0487 0.1236 1.0000
11.250 1.2944 0.03079 0.02432 -0.0442 0.0768 1.0000
11.500 1.2716 0.03475 0.02814 -0.0411 0.0394 1.0000
11.750 1.2623 0.03781 0.03116 -0.0392 0.0186 1.0000
12.000 1.2665 0.03980 0.03320 -0.0383 0.0163 1.0000
12.250 1.2723 0.04169 0.03513 -0.0375 0.0151 1.0000
12.500 1.2778 0.04362 0.03712 -0.0368 0.0144 1.0000
12.750 1.2828 0.04566 0.03921 -0.0361 0.0139 1.0000
13.000 1.2851 0.04799 0.04160 -0.0354 0.0132 1.0000
13.250 1.2865 0.05047 0.04415 -0.0348 0.0127 1.0000
13.500 1.2874 0.05303 0.04678 -0.0342 0.0123 1.0000
13.750 1.2909 0.05537 0.04919 -0.0338 0.0121 1.0000
14.000 1.2931 0.05789 0.05176 -0.0335 0.0117 1.0000
14.250 1.2945 0.06053 0.05448 -0.0332 0.0113 1.0000
14.500 1.2955 0.06326 0.05727 -0.0329 0.0113 1.0000
14.750 1.2940 0.06628 0.06037 -0.0327 0.0110 1.0000
15.000 1.2928 0.06935 0.06350 -0.0326 0.0107 1.0000
15.250 1.2897 0.07268 0.06690 -0.0325 0.0104 1.0000
15.500 1.2846 0.07629 0.07059 -0.0325 0.0102 1.0000
15.750 1.2769 0.08026 0.07466 -0.0326 0.0101 1.0000
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