GOE 646 AIRFOIL (goe646-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 646 AIRFOIL (goe646-il) Reynolds number: 200,000 Max Cl/Cd: 65.24 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe646-il-200000-n5.txt Download as CSV file: xf-goe646-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 646 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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.6813 0.09503 0.08985 -0.0789 1.0000 0.0500
-16.500 -0.7139 0.08682 0.08144 -0.0831 1.0000 0.0506
-16.250 -0.7232 0.08275 0.07732 -0.0846 1.0000 0.0511
-16.000 -0.7265 0.07978 0.07435 -0.0853 1.0000 0.0516
-15.750 -0.7338 0.07632 0.07087 -0.0863 1.0000 0.0522
-15.500 -0.7430 0.07278 0.06728 -0.0873 1.0000 0.0527
-15.250 -0.7542 0.06919 0.06365 -0.0881 1.0000 0.0533
-15.000 -0.7668 0.06582 0.06022 -0.0886 1.0000 0.0538
-14.750 -0.7806 0.06268 0.05703 -0.0885 1.0000 0.0544
-14.500 -0.7964 0.05972 0.05402 -0.0880 1.0000 0.0548
-14.250 -0.7947 0.05602 0.05020 -0.0914 0.9978 0.0557
-14.000 -0.7866 0.05251 0.04660 -0.0955 0.9942 0.0567
-13.750 -0.7775 0.04934 0.04340 -0.0992 0.9901 0.0576
-13.500 -0.7687 0.04615 0.04015 -0.1030 0.9852 0.0586
-13.250 -0.7571 0.04307 0.03697 -0.1072 0.9811 0.0599
-13.000 -0.7505 0.04021 0.03400 -0.1100 0.9745 0.0612
-12.750 -0.7384 0.03745 0.03112 -0.1136 0.9692 0.0627
-12.500 -0.7300 0.03492 0.02855 -0.1163 0.9615 0.0639
-12.250 -0.7146 0.03250 0.02605 -0.1199 0.9552 0.0655
-12.000 -0.7044 0.03038 0.02380 -0.1220 0.9455 0.0672
-11.750 -0.6850 0.02860 0.02187 -0.1245 0.9393 0.0692
-11.500 -0.6755 0.02729 0.02052 -0.1240 0.9299 0.0706
-11.250 -0.6522 0.02608 0.01923 -0.1254 0.9250 0.0730
-11.000 -0.6224 0.02502 0.01802 -0.1274 0.9221 0.0762
-10.750 -0.6078 0.02414 0.01713 -0.1266 0.9143 0.0782
-10.500 -0.5820 0.02328 0.01621 -0.1276 0.9096 0.0812
-10.250 -0.5513 0.02248 0.01529 -0.1292 0.9062 0.0846
-10.000 -0.5231 0.02164 0.01444 -0.1304 0.9023 0.0877
-9.750 -0.5057 0.02112 0.01385 -0.1291 0.8947 0.0907
-9.500 -0.4781 0.02047 0.01313 -0.1298 0.8898 0.0942
-9.250 -0.4460 0.01978 0.01242 -0.1314 0.8861 0.0984
-9.000 -0.4244 0.01936 0.01192 -0.1306 0.8797 0.1023
-8.750 -0.4030 0.01885 0.01141 -0.1299 0.8731 0.1061
-8.500 -0.3733 0.01837 0.01086 -0.1306 0.8682 0.1112
-8.250 -0.3443 0.01787 0.01035 -0.1313 0.8633 0.1166
-8.000 -0.3261 0.01756 0.01000 -0.1296 0.8551 0.1221
-7.750 -0.2990 0.01713 0.00956 -0.1297 0.8490 0.1289
-7.500 -0.2677 0.01673 0.00911 -0.1306 0.8442 0.1374
-7.250 -0.2502 0.01645 0.00885 -0.1287 0.8358 0.1451
-7.000 -0.2238 0.01611 0.00850 -0.1286 0.8293 0.1541
-6.750 -0.1937 0.01580 0.00813 -0.1290 0.8237 0.1638
-6.500 -0.1743 0.01556 0.00791 -0.1274 0.8146 0.1724
-6.250 -0.1459 0.01528 0.00759 -0.1275 0.8076 0.1819
-6.000 -0.1214 0.01508 0.00735 -0.1268 0.7994 0.1915
-5.750 -0.0964 0.01486 0.00714 -0.1262 0.7908 0.2007
-5.500 -0.0681 0.01467 0.00689 -0.1262 0.7835 0.2103
-5.250 -0.0450 0.01452 0.00675 -0.1252 0.7740 0.2190
-5.000 -0.0156 0.01436 0.00651 -0.1253 0.7664 0.2283
-4.750 0.0071 0.01425 0.00640 -0.1242 0.7560 0.2370
-4.500 0.0359 0.01413 0.00619 -0.1242 0.7473 0.2455
-4.250 0.0593 0.01404 0.00609 -0.1231 0.7361 0.2536
-4.000 0.0868 0.01395 0.00591 -0.1229 0.7264 0.2619
-3.750 0.1115 0.01388 0.00583 -0.1221 0.7156 0.2695
-3.500 0.1387 0.01383 0.00568 -0.1218 0.7063 0.2779
-3.250 0.1639 0.01378 0.00562 -0.1211 0.6963 0.2861
-3.000 0.1908 0.01378 0.00553 -0.1207 0.6875 0.2960
-2.750 0.2161 0.01375 0.00549 -0.1201 0.6783 0.3040
-2.500 0.2431 0.01375 0.00541 -0.1197 0.6702 0.3119
-2.250 0.2685 0.01375 0.00534 -0.1191 0.6613 0.3185
-2.000 0.2950 0.01373 0.00529 -0.1187 0.6538 0.3243
-1.750 0.3208 0.01374 0.00527 -0.1181 0.6468 0.3311
-1.500 0.3470 0.01378 0.00523 -0.1176 0.6399 0.3377
-1.000 0.3981 0.01380 0.00522 -0.1164 0.6254 0.3502
-0.750 0.4236 0.01386 0.00518 -0.1158 0.6174 0.3572
-0.500 0.4489 0.01388 0.00520 -0.1152 0.6103 0.3634
-0.250 0.4730 0.01390 0.00523 -0.1143 0.6028 0.3704
0.000 0.4987 0.01398 0.00522 -0.1137 0.5957 0.3778
0.250 0.5230 0.01400 0.00527 -0.1129 0.5892 0.3848
0.500 0.5472 0.01403 0.00532 -0.1121 0.5829 0.3926
0.750 0.5727 0.01410 0.00535 -0.1115 0.5774 0.4005
1.000 0.5983 0.01415 0.00541 -0.1110 0.5724 0.4085
1.250 0.6220 0.01419 0.00550 -0.1101 0.5671 0.4172
1.500 0.6461 0.01423 0.00558 -0.1093 0.5618 0.4259
1.750 0.6709 0.01429 0.00565 -0.1086 0.5566 0.4364
2.000 0.6953 0.01435 0.00574 -0.1078 0.5515 0.4472
2.250 0.7175 0.01440 0.00587 -0.1066 0.5457 0.4593
2.500 0.7406 0.01445 0.00599 -0.1056 0.5403 0.4733
2.750 0.7646 0.01452 0.00610 -0.1048 0.5353 0.4909
3.000 0.7864 0.01458 0.00626 -0.1035 0.5298 0.5119
3.250 0.8070 0.01463 0.00643 -0.1020 0.5235 0.5362
3.500 0.8285 0.01471 0.00657 -0.1007 0.5176 0.5633
3.750 0.8498 0.01480 0.00674 -0.0993 0.5120 0.5927
4.000 0.8680 0.01487 0.00693 -0.0973 0.5055 0.6204
4.250 0.8866 0.01495 0.00706 -0.0954 0.4986 0.6464
4.500 0.9039 0.01505 0.00720 -0.0932 0.4909 0.6698
4.750 0.9188 0.01515 0.00737 -0.0907 0.4814 0.6917
5.000 0.9343 0.01526 0.00754 -0.0882 0.4724 0.7163
5.250 0.9499 0.01537 0.00776 -0.0858 0.4617 0.7466
5.500 0.9698 0.01544 0.00801 -0.0842 0.4522 0.8023
5.750 1.0165 0.01558 0.00832 -0.0884 0.4398 1.0000
6.000 1.0331 0.01585 0.00858 -0.0864 0.4293 1.0000
6.250 1.0478 0.01617 0.00883 -0.0842 0.4186 1.0000
6.500 1.0621 0.01652 0.00913 -0.0819 0.4062 1.0000
6.750 1.0761 0.01691 0.00947 -0.0796 0.3940 1.0000
7.000 1.0886 0.01737 0.00986 -0.0772 0.3819 1.0000
7.250 1.1009 0.01787 0.01029 -0.0748 0.3704 1.0000
7.500 1.1144 0.01838 0.01075 -0.0727 0.3602 1.0000
7.750 1.1263 0.01898 0.01128 -0.0704 0.3510 1.0000
8.000 1.1407 0.01953 0.01180 -0.0686 0.3425 1.0000
8.250 1.1527 0.02018 0.01240 -0.0665 0.3341 1.0000
8.500 1.1661 0.02082 0.01301 -0.0646 0.3259 1.0000
8.750 1.1783 0.02153 0.01368 -0.0627 0.3179 1.0000
9.000 1.1907 0.02225 0.01438 -0.0608 0.3104 1.0000
9.250 1.2031 0.02300 0.01511 -0.0591 0.3022 1.0000
9.500 1.2137 0.02386 0.01591 -0.0571 0.2954 1.0000
9.750 1.2276 0.02458 0.01668 -0.0557 0.2881 1.0000
10.000 1.2383 0.02548 0.01756 -0.0539 0.2811 1.0000
10.250 1.2504 0.02635 0.01843 -0.0524 0.2748 1.0000
10.500 1.2634 0.02718 0.01930 -0.0510 0.2689 1.0000
10.750 1.2739 0.02817 0.02029 -0.0495 0.2630 1.0000
11.000 1.2855 0.02914 0.02127 -0.0481 0.2578 1.0000
11.250 1.2974 0.03011 0.02229 -0.0468 0.2517 1.0000
11.500 1.3058 0.03130 0.02348 -0.0453 0.2455 1.0000
11.750 1.3161 0.03243 0.02464 -0.0440 0.2397 1.0000
12.000 1.3260 0.03361 0.02587 -0.0428 0.2338 1.0000
12.250 1.3332 0.03501 0.02726 -0.0415 0.2283 1.0000
12.500 1.3427 0.03629 0.02861 -0.0404 0.2225 1.0000
12.750 1.3505 0.03774 0.03010 -0.0393 0.2165 1.0000
13.250 1.3646 0.04089 0.03331 -0.0373 0.2053 1.0000
13.500 1.3700 0.04267 0.03511 -0.0363 0.1994 1.0000
13.750 1.3749 0.04453 0.03699 -0.0355 0.1940 1.0000
14.000 1.3814 0.04633 0.03885 -0.0348 0.1884 1.0000
14.250 1.3847 0.04844 0.04098 -0.0341 0.1832 1.0000
14.500 1.3897 0.05043 0.04303 -0.0335 0.1783 1.0000
14.750 1.3943 0.05252 0.04517 -0.0329 0.1731 1.0000
15.000 1.3953 0.05498 0.04765 -0.0324 0.1681 1.0000
15.250 1.3995 0.05719 0.04993 -0.0321 0.1630 1.0000
15.500 1.4010 0.05973 0.05252 -0.0318 0.1573 1.0000
15.750 1.4005 0.06249 0.05530 -0.0315 0.1522 1.0000
16.000 1.4023 0.06508 0.05797 -0.0314 0.1460 1.0000
16.250 1.3982 0.06837 0.06126 -0.0314 0.1402 1.0000
16.500 1.3996 0.07110 0.06409 -0.0314 0.1335 1.0000
16.750 1.3952 0.07455 0.06757 -0.0316 0.1271 1.0000
17.000 1.3928 0.07782 0.07091 -0.0318 0.1200 1.0000
17.250 1.3877 0.08146 0.07459 -0.0322 0.1134 1.0000
17.500 1.3808 0.08542 0.07857 -0.0328 0.1070 1.0000
17.750 1.3744 0.08936 0.08256 -0.0334 0.1018 1.0000
18.000 1.3664 0.09357 0.08680 -0.0343 0.0975 1.0000
18.250 1.3597 0.09766 0.09093 -0.0351 0.0941 1.0000
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