GOE 670 AIRFOIL (goe670-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 670 AIRFOIL (goe670-il) Reynolds number: 200,000 Max Cl/Cd: 70.49 at α=3.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe670-il-200000-n5.txt Download as CSV file: xf-goe670-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 670 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 -0.4453 0.08678 0.08317 -0.0391 1.0000 0.0312
-9.000 -0.4617 0.08345 0.07990 -0.0383 1.0000 0.0313
-8.750 -0.4842 0.08057 0.07712 -0.0366 1.0000 0.0315
-8.500 -0.4762 0.07630 0.07284 -0.0420 0.9950 0.0321
-8.250 -0.4564 0.07473 0.07125 -0.0444 0.9915 0.0330
-8.000 -0.4381 0.07104 0.06752 -0.0497 0.9868 0.0342
-7.750 -0.4269 0.06475 0.06115 -0.0571 0.9803 0.0350
-7.500 -0.4141 0.05695 0.05318 -0.0654 0.9749 0.0356
-7.250 -0.4061 0.04877 0.04473 -0.0710 0.9676 0.0366
-7.000 -0.4130 0.03368 0.02860 -0.0755 0.9584 0.0386
-6.750 -0.3948 0.02836 0.02248 -0.0767 0.9547 0.0394
-6.500 -0.3772 0.02582 0.01949 -0.0759 0.9494 0.0400
-6.250 -0.3517 0.02419 0.01766 -0.0763 0.9457 0.0411
-6.000 -0.3210 0.02317 0.01650 -0.0774 0.9433 0.0422
-5.750 -0.2927 0.02196 0.01506 -0.0779 0.9405 0.0431
-5.500 -0.2704 0.02088 0.01375 -0.0770 0.9353 0.0439
-5.250 -0.2412 0.01978 0.01243 -0.0776 0.9326 0.0449
-5.000 -0.2093 0.01879 0.01123 -0.0785 0.9305 0.0460
-4.750 -0.1763 0.01789 0.01014 -0.0796 0.9289 0.0472
-4.500 -0.1558 0.01728 0.00940 -0.0781 0.9225 0.0482
-4.250 -0.1259 0.01669 0.00868 -0.0785 0.9194 0.0495
-4.000 -0.0947 0.01595 0.00789 -0.0793 0.9170 0.0516
-3.750 -0.0618 0.01544 0.00737 -0.0804 0.9150 0.0539
-3.500 -0.0412 0.01510 0.00700 -0.0788 0.9080 0.0558
-3.250 -0.0110 0.01465 0.00649 -0.0792 0.9043 0.0585
-3.000 0.0216 0.01421 0.00598 -0.0800 0.9014 0.0615
-2.750 0.0457 0.01387 0.00571 -0.0792 0.8954 0.0655
-2.500 0.0736 0.01361 0.00544 -0.0791 0.8904 0.0709
-2.250 0.1052 0.01332 0.00518 -0.0798 0.8869 0.0784
-2.000 0.1326 0.01317 0.00500 -0.0795 0.8814 0.0875
-1.750 0.1594 0.01295 0.00484 -0.0792 0.8749 0.0966
-1.500 0.1913 0.01269 0.00457 -0.0799 0.8706 0.1060
-1.250 0.2160 0.01254 0.00443 -0.0791 0.8620 0.1157
-1.000 0.2473 0.01224 0.00417 -0.0796 0.8552 0.1265
-0.750 0.2722 0.01205 0.00400 -0.0788 0.8442 0.1363
-0.250 0.3293 0.01155 0.00356 -0.0786 0.8228 0.1639
0.000 0.3552 0.01127 0.00338 -0.0779 0.8071 0.1937
0.250 0.3790 0.01090 0.00327 -0.0769 0.7898 0.2759
0.500 0.3948 0.00992 0.00317 -0.0745 0.7719 0.5584
1.000 0.5403 0.00921 0.00320 -0.0924 0.7273 0.9958
1.250 0.5724 0.00927 0.00313 -0.0932 0.7064 1.0000
1.500 0.5952 0.00937 0.00308 -0.0919 0.6858 1.0000
1.750 0.6175 0.00950 0.00307 -0.0906 0.6656 1.0000
2.000 0.6395 0.00966 0.00310 -0.0893 0.6470 1.0000
2.250 0.6614 0.00983 0.00316 -0.0879 0.6304 1.0000
2.500 0.6832 0.01001 0.00326 -0.0866 0.6144 1.0000
2.750 0.7049 0.01020 0.00337 -0.0852 0.5977 1.0000
3.000 0.7260 0.01040 0.00350 -0.0837 0.5790 1.0000
3.250 0.7464 0.01059 0.00363 -0.0821 0.5538 1.0000
3.500 0.7648 0.01085 0.00376 -0.0800 0.5153 1.0000
3.750 0.7796 0.01125 0.00390 -0.0773 0.4598 1.0000
4.000 0.7926 0.01178 0.00412 -0.0744 0.4080 1.0000
4.250 0.8082 0.01226 0.00440 -0.0719 0.3691 1.0000
4.500 0.8251 0.01270 0.00469 -0.0699 0.3385 1.0000
4.750 0.8431 0.01311 0.00500 -0.0680 0.3154 1.0000
5.000 0.8617 0.01350 0.00530 -0.0662 0.2965 1.0000
5.250 0.8808 0.01388 0.00562 -0.0645 0.2819 1.0000
5.500 0.8999 0.01426 0.00596 -0.0629 0.2698 1.0000
5.750 0.9198 0.01461 0.00630 -0.0614 0.2599 1.0000
6.000 0.9398 0.01496 0.00666 -0.0600 0.2526 1.0000
6.250 0.9597 0.01532 0.00702 -0.0585 0.2442 1.0000
6.500 0.9793 0.01570 0.00740 -0.0570 0.2337 1.0000
6.750 0.9979 0.01611 0.00779 -0.0554 0.2212 1.0000
7.000 1.0163 0.01652 0.00816 -0.0538 0.2076 1.0000
7.250 1.0359 0.01687 0.00854 -0.0523 0.1957 1.0000
7.500 1.0551 0.01723 0.00891 -0.0509 0.1818 1.0000
7.750 1.0740 0.01761 0.00933 -0.0493 0.1678 1.0000
8.000 1.0914 0.01805 0.00973 -0.0476 0.1462 1.0000
8.250 1.1026 0.01886 0.01026 -0.0450 0.1020 1.0000
8.500 1.1117 0.01993 0.01111 -0.0421 0.0737 1.0000
8.750 1.1198 0.02113 0.01208 -0.0392 0.0399 1.0000
9.000 1.1306 0.02212 0.01304 -0.0365 0.0320 1.0000
9.250 1.1428 0.02298 0.01400 -0.0342 0.0284 1.0000
9.500 1.1521 0.02403 0.01513 -0.0315 0.0258 1.0000
9.750 1.1636 0.02491 0.01612 -0.0292 0.0242 1.0000
10.000 1.1745 0.02582 0.01715 -0.0269 0.0225 1.0000
10.250 1.1838 0.02685 0.01827 -0.0246 0.0211 1.0000
10.500 1.1902 0.02809 0.01959 -0.0221 0.0199 1.0000
10.750 1.1922 0.02964 0.02124 -0.0192 0.0191 1.0000
11.000 1.1980 0.03099 0.02271 -0.0169 0.0186 1.0000
11.250 1.2037 0.03240 0.02427 -0.0147 0.0179 1.0000
11.500 1.2085 0.03394 0.02592 -0.0126 0.0174 1.0000
11.750 1.2131 0.03555 0.02764 -0.0107 0.0167 1.0000
12.000 1.2169 0.03727 0.02947 -0.0090 0.0161 1.0000
12.250 1.2206 0.03906 0.03136 -0.0074 0.0155 1.0000
12.500 1.2231 0.04102 0.03340 -0.0061 0.0149 1.0000
12.750 1.2241 0.04322 0.03569 -0.0048 0.0146 1.0000
13.000 1.2216 0.04590 0.03845 -0.0035 0.0141 1.0000
13.250 1.2201 0.04865 0.04128 -0.0024 0.0139 1.0000
13.500 1.2220 0.05108 0.04386 -0.0017 0.0137 1.0000
13.750 1.2230 0.05372 0.04668 -0.0011 0.0135 1.0000
14.000 1.2228 0.05658 0.04970 -0.0008 0.0132 1.0000
14.250 1.2223 0.05956 0.05284 -0.0006 0.0130 1.0000
14.500 1.2204 0.06282 0.05626 -0.0006 0.0128 1.0000
14.750 1.2174 0.06631 0.05992 -0.0009 0.0126 1.0000
15.000 1.2135 0.07004 0.06381 -0.0015 0.0124 1.0000
15.250 1.2079 0.07410 0.06804 -0.0025 0.0121 1.0000
15.500 1.2012 0.07852 0.07264 -0.0038 0.0120 1.0000
15.750 1.1932 0.08328 0.07756 -0.0056 0.0117 1.0000
16.000 1.1850 0.08828 0.08272 -0.0078 0.0115 1.0000
16.250 1.1760 0.09363 0.08824 -0.0102 0.0114 1.0000
16.500 1.1644 0.09969 0.09448 -0.0130 0.0114 1.0000
16.750 1.1547 0.10558 0.10051 -0.0162 0.0112 1.0000
17.000 1.1411 0.11252 0.10764 -0.0199 0.0113 1.0000
17.250 1.1305 0.11902 0.11428 -0.0237 0.0110 1.0000
17.500 1.1148 0.12693 0.12237 -0.0282 0.0111 1.0000
17.750 1.1004 0.13476 0.13037 -0.0330 0.0110 1.0000
18.000 1.0786 0.14487 0.14068 -0.0391 0.0112 1.0000
18.250 1.0600 0.15458 0.15055 -0.0451 0.0112 1.0000
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Polar data table (+)
Polar graphs
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