GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 275 (DAIMLER VI) AIRFOIL (goe275-il) Reynolds number: 1,000,000 Max Cl/Cd: 118.15 at α=5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe275-il-1000000.txt Download as CSV file: xf-goe275-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 275 (DAIMLER VI) 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
------ -------- --------- --------- -------- -------- --------
-8.750 -0.3380 0.09835 0.09674 -0.0214 1.0000 0.0132
-8.500 -0.3403 0.09565 0.09407 -0.0217 1.0000 0.0133
-8.250 -0.3454 0.09325 0.09170 -0.0212 1.0000 0.0133
-8.000 -0.3402 0.08946 0.08793 -0.0251 0.9986 0.0133
-7.750 -0.3246 0.08504 0.08351 -0.0281 0.9967 0.0135
-7.500 -0.3049 0.08193 0.08040 -0.0314 0.9947 0.0137
-7.250 -0.2830 0.07799 0.07646 -0.0372 0.9908 0.0140
-7.000 -0.2579 0.07399 0.07245 -0.0438 0.9872 0.0144
-6.750 -0.2298 0.06953 0.06797 -0.0516 0.9846 0.0151
-6.500 -0.1956 0.06306 0.06144 -0.0645 0.9763 0.0162
-6.250 -0.1583 0.05634 0.05461 -0.0755 0.9726 0.0163
-5.500 -0.0872 0.04632 0.04448 -0.0851 0.9508 0.0171
-5.250 -0.0469 0.04264 0.04070 -0.0916 0.9457 0.0180
-5.000 0.0054 0.03616 0.03385 -0.0996 0.9360 0.0197
-4.750 0.0357 0.03112 0.02858 -0.1035 0.9257 0.0199
-4.500 0.0638 0.02924 0.02661 -0.1054 0.9147 0.0202
-4.250 0.0894 0.02759 0.02484 -0.1062 0.9029 0.0205
-4.000 0.1137 0.02594 0.02305 -0.1064 0.8903 0.0211
-3.750 0.1443 0.02406 0.02077 -0.1055 0.8784 0.0235
-3.500 0.1683 0.02235 0.01879 -0.1048 0.8644 0.0236
-3.250 0.1884 0.01902 0.01518 -0.1041 0.8499 0.0239
-3.000 0.2112 0.01778 0.01383 -0.1036 0.8332 0.0242
-2.750 0.2346 0.01682 0.01275 -0.1029 0.8141 0.0246
-2.500 0.2580 0.01604 0.01181 -0.1021 0.7918 0.0253
-2.250 0.2814 0.01528 0.01082 -0.1010 0.7617 0.0266
-2.000 0.3067 0.01570 0.01080 -0.0993 0.7199 0.0282
-1.750 0.3288 0.01523 0.00997 -0.0978 0.6736 0.0283
-1.500 0.3497 0.01308 0.00756 -0.0968 0.6377 0.0291
-1.250 0.3732 0.01256 0.00688 -0.0959 0.6063 0.0296
-1.000 0.3977 0.01215 0.00632 -0.0952 0.5781 0.0303
-0.750 0.4225 0.01187 0.00587 -0.0944 0.5496 0.0317
-0.500 0.4481 0.01244 0.00618 -0.0935 0.5148 0.0338
-0.250 0.4716 0.01128 0.00477 -0.0926 0.4775 0.0352
0.000 0.4956 0.01100 0.00436 -0.0919 0.4388 0.0364
0.250 0.5204 0.01090 0.00410 -0.0912 0.4078 0.0383
0.500 0.5464 0.01148 0.00451 -0.0905 0.3846 0.0410
0.750 0.5708 0.01048 0.00348 -0.0900 0.3678 0.0445
1.000 0.5964 0.01040 0.00335 -0.0894 0.3540 0.0475
1.250 0.6216 0.01013 0.00305 -0.0889 0.3435 0.0548
1.500 0.6481 0.01013 0.00304 -0.0885 0.3364 0.0600
1.750 0.6746 0.00987 0.00262 -0.0875 0.3306 0.0344
2.000 0.7007 0.00980 0.00254 -0.0870 0.3247 0.0342
2.250 0.7267 0.00964 0.00237 -0.0865 0.3194 0.0343
2.500 0.7525 0.00957 0.00228 -0.0861 0.3140 0.0347
2.750 0.7787 0.00954 0.00223 -0.0856 0.3092 0.0350
3.000 0.8052 0.00950 0.00221 -0.0853 0.3045 0.0365
3.250 0.8312 0.00955 0.00223 -0.0848 0.2980 0.0372
3.500 0.8575 0.00959 0.00226 -0.0844 0.2930 0.0382
3.750 0.8840 0.00963 0.00230 -0.0841 0.2879 0.0402
4.000 0.9100 0.00972 0.00236 -0.0837 0.2818 0.0429
4.250 0.9431 0.00817 0.00272 -0.0855 0.2759 1.0000
4.500 0.9688 0.00831 0.00280 -0.0850 0.2681 1.0000
4.750 0.9944 0.00845 0.00291 -0.0845 0.2601 1.0000
5.000 1.0196 0.00863 0.00303 -0.0839 0.2478 1.0000
5.250 1.0438 0.00889 0.00317 -0.0833 0.2249 1.0000
5.500 1.0662 0.00931 0.00341 -0.0823 0.1931 1.0000
5.750 1.0897 0.00965 0.00366 -0.0815 0.1781 1.0000
6.000 1.1138 0.00991 0.00388 -0.0808 0.1699 1.0000
6.250 1.1381 0.01016 0.00411 -0.0802 0.1629 1.0000
6.500 1.1624 0.01041 0.00435 -0.0795 0.1562 1.0000
6.750 1.1865 0.01068 0.00459 -0.0789 0.1483 1.0000
7.000 1.2099 0.01100 0.00486 -0.0781 0.1361 1.0000
7.250 1.2309 0.01155 0.00520 -0.0770 0.1019 1.0000
7.500 1.2518 0.01210 0.00564 -0.0759 0.0861 1.0000
7.750 1.2748 0.01243 0.00598 -0.0751 0.0827 1.0000
8.000 1.2972 0.01282 0.00636 -0.0742 0.0793 1.0000
8.250 1.3191 0.01324 0.00679 -0.0732 0.0751 1.0000
8.500 1.3422 0.01353 0.00712 -0.0724 0.0731 1.0000
8.750 1.3654 0.01379 0.00742 -0.0717 0.0718 1.0000
9.000 1.3882 0.01408 0.00776 -0.0709 0.0698 1.0000
9.250 1.4100 0.01444 0.00814 -0.0700 0.0674 1.0000
9.500 1.4309 0.01486 0.00857 -0.0689 0.0642 1.0000
9.750 1.4517 0.01526 0.00902 -0.0678 0.0616 1.0000
10.000 1.4750 0.01545 0.00924 -0.0672 0.0596 1.0000
10.250 1.4963 0.01577 0.00957 -0.0662 0.0558 1.0000
10.500 1.5161 0.01620 0.00997 -0.0651 0.0505 1.0000
10.750 1.5337 0.01677 0.01045 -0.0636 0.0390 1.0000
11.000 1.5408 0.01805 0.01154 -0.0605 0.0194 1.0000
11.250 1.5510 0.01889 0.01240 -0.0577 0.0158 1.0000
11.500 1.5607 0.01967 0.01323 -0.0548 0.0141 1.0000
11.750 1.5729 0.02029 0.01393 -0.0524 0.0134 1.0000
12.000 1.5831 0.02104 0.01476 -0.0498 0.0127 1.0000
12.250 1.5916 0.02190 0.01568 -0.0471 0.0120 1.0000
12.500 1.5956 0.02304 0.01692 -0.0439 0.0112 1.0000
12.750 1.6027 0.02402 0.01798 -0.0413 0.0108 1.0000
13.000 1.6108 0.02495 0.01900 -0.0390 0.0105 1.0000
13.250 1.6172 0.02604 0.02017 -0.0367 0.0101 1.0000
13.500 1.6216 0.02732 0.02154 -0.0344 0.0097 1.0000
13.750 1.6249 0.02874 0.02305 -0.0322 0.0094 1.0000
14.000 1.6263 0.03040 0.02480 -0.0302 0.0092 1.0000
14.250 1.6243 0.03244 0.02694 -0.0282 0.0090 1.0000
14.500 1.6192 0.03493 0.02954 -0.0265 0.0087 1.0000
14.750 1.6063 0.03841 0.03317 -0.0251 0.0084 1.0000
15.000 1.5964 0.04198 0.03688 -0.0245 0.0083 1.0000
15.250 1.5954 0.04482 0.03983 -0.0245 0.0082 1.0000
15.500 1.5880 0.04871 0.04384 -0.0250 0.0082 1.0000
15.750 1.5798 0.05297 0.04823 -0.0260 0.0081 1.0000
16.000 1.5713 0.05749 0.05288 -0.0273 0.0080 1.0000
16.250 1.5578 0.06299 0.05851 -0.0293 0.0079 1.0000
16.500 1.5447 0.06861 0.06427 -0.0314 0.0078 1.0000
16.750 1.5280 0.07502 0.07081 -0.0341 0.0078 1.0000
17.000 1.5110 0.08165 0.07758 -0.0369 0.0078 1.0000
17.250 1.4945 0.08832 0.08437 -0.0399 0.0077 1.0000
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