GOE 692 AIRFOIL (goe692-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 692 AIRFOIL (goe692-il) Reynolds number: 200,000 Max Cl/Cd: 73.64 at α=5.75° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe692-il-200000-n5.txt Download as CSV file: xf-goe692-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 692 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
------ -------- --------- --------- -------- -------- --------
-12.250 -0.6142 0.04197 0.03685 -0.1278 0.9587 0.0408
-12.000 -0.6234 0.03840 0.03298 -0.1288 0.9461 0.0411
-11.750 -0.6203 0.03566 0.02993 -0.1291 0.9374 0.0415
-11.500 -0.6112 0.03335 0.02731 -0.1292 0.9298 0.0420
-11.250 -0.5985 0.03137 0.02502 -0.1291 0.9231 0.0426
-11.000 -0.5825 0.02992 0.02340 -0.1286 0.9160 0.0431
-10.750 -0.5592 0.02887 0.02228 -0.1290 0.9115 0.0437
-10.500 -0.5398 0.02802 0.02137 -0.1285 0.9046 0.0443
-10.250 -0.5185 0.02712 0.02035 -0.1282 0.8988 0.0451
-10.000 -0.4947 0.02612 0.01919 -0.1284 0.8944 0.0460
-9.750 -0.4750 0.02519 0.01809 -0.1276 0.8878 0.0470
-9.500 -0.4533 0.02421 0.01691 -0.1271 0.8819 0.0479
-9.250 -0.4285 0.02334 0.01591 -0.1271 0.8773 0.0488
-9.000 -0.4061 0.02274 0.01527 -0.1266 0.8713 0.0497
-8.750 -0.3826 0.02215 0.01461 -0.1262 0.8656 0.0508
-8.500 -0.3571 0.02151 0.01385 -0.1261 0.8610 0.0521
-8.250 -0.3324 0.02089 0.01308 -0.1257 0.8559 0.0538
-8.000 -0.3089 0.02037 0.01251 -0.1252 0.8496 0.0554
-7.750 -0.2830 0.01993 0.01202 -0.1251 0.8444 0.0572
-7.500 -0.2561 0.01946 0.01143 -0.1250 0.8400 0.0595
-7.250 -0.2323 0.01901 0.01089 -0.1244 0.8338 0.0617
-7.000 -0.2067 0.01861 0.01047 -0.1242 0.8285 0.0639
-6.750 -0.1794 0.01821 0.00997 -0.1242 0.8239 0.0668
-6.500 -0.1541 0.01784 0.00953 -0.1238 0.8181 0.0699
-6.250 -0.1286 0.01752 0.00919 -0.1234 0.8120 0.0731
-6.000 -0.1011 0.01721 0.00876 -0.1234 0.8070 0.0770
-5.750 -0.0747 0.01687 0.00841 -0.1232 0.8021 0.0804
-5.500 -0.0492 0.01661 0.00812 -0.1229 0.7958 0.0842
-5.250 -0.0220 0.01633 0.00776 -0.1227 0.7902 0.0882
-5.000 0.0054 0.01605 0.00747 -0.1227 0.7853 0.0925
-4.750 0.0311 0.01586 0.00724 -0.1223 0.7786 0.0973
-4.500 0.0580 0.01562 0.00702 -0.1222 0.7730 0.1025
-4.250 0.0863 0.01544 0.00676 -0.1222 0.7681 0.1087
-4.000 0.1118 0.01526 0.00663 -0.1218 0.7611 0.1146
-3.750 0.1392 0.01510 0.00642 -0.1217 0.7552 0.1217
-3.500 0.1670 0.01491 0.00623 -0.1217 0.7501 0.1286
-3.250 0.1931 0.01479 0.00609 -0.1213 0.7430 0.1366
-3.000 0.2204 0.01462 0.00594 -0.1212 0.7371 0.1450
-2.750 0.2480 0.01450 0.00577 -0.1211 0.7313 0.1542
-2.500 0.2743 0.01438 0.00568 -0.1208 0.7243 0.1636
-2.250 0.3021 0.01426 0.00552 -0.1208 0.7186 0.1733
-2.000 0.3289 0.01417 0.00544 -0.1206 0.7122 0.1834
-1.750 0.3557 0.01407 0.00534 -0.1203 0.7057 0.1928
-1.500 0.3838 0.01399 0.00521 -0.1203 0.7004 0.2036
-1.250 0.4100 0.01391 0.00518 -0.1201 0.6940 0.2148
-1.000 0.4371 0.01383 0.00511 -0.1199 0.6880 0.2270
-0.750 0.4651 0.01376 0.00502 -0.1199 0.6830 0.2414
-0.500 0.4911 0.01369 0.00503 -0.1196 0.6767 0.2588
-0.250 0.5178 0.01359 0.00501 -0.1195 0.6709 0.2840
0.000 0.5451 0.01344 0.00496 -0.1194 0.6660 0.3254
0.500 0.5935 0.01287 0.00510 -0.1183 0.6544 0.5209
0.750 0.6161 0.01249 0.00518 -0.1171 0.6495 0.6704
1.000 0.6372 0.01227 0.00538 -0.1150 0.6440 0.8109
1.250 0.6718 0.01229 0.00553 -0.1159 0.6381 0.9114
1.500 0.7132 0.01239 0.00556 -0.1186 0.6328 0.9590
1.750 0.7531 0.01252 0.00564 -0.1212 0.6271 0.9855
2.000 0.7913 0.01265 0.00572 -0.1236 0.6209 1.0000
2.250 0.8148 0.01277 0.00575 -0.1227 0.6155 1.0000
2.500 0.8375 0.01291 0.00584 -0.1218 0.6097 1.0000
2.750 0.8597 0.01305 0.00595 -0.1207 0.6033 1.0000
3.000 0.8838 0.01319 0.00601 -0.1200 0.5973 1.0000
3.250 0.9056 0.01333 0.00614 -0.1188 0.5893 1.0000
3.500 0.9280 0.01348 0.00621 -0.1178 0.5805 1.0000
3.750 0.9497 0.01363 0.00634 -0.1166 0.5716 1.0000
4.000 0.9723 0.01379 0.00645 -0.1156 0.5635 1.0000
4.250 0.9949 0.01396 0.00660 -0.1146 0.5561 1.0000
4.500 1.0167 0.01414 0.00676 -0.1135 0.5476 1.0000
4.750 1.0384 0.01433 0.00692 -0.1124 0.5389 1.0000
5.000 1.0590 0.01452 0.00708 -0.1111 0.5288 1.0000
5.250 1.0794 0.01473 0.00728 -0.1097 0.5188 1.0000
5.500 1.0996 0.01496 0.00744 -0.1083 0.5091 1.0000
5.750 1.1186 0.01519 0.00768 -0.1068 0.4981 1.0000
6.000 1.1372 0.01546 0.00792 -0.1051 0.4874 1.0000
6.250 1.1537 0.01575 0.00815 -0.1031 0.4761 1.0000
6.500 1.1691 0.01606 0.00844 -0.1009 0.4643 1.0000
6.750 1.1842 0.01642 0.00876 -0.0987 0.4527 1.0000
7.000 1.1990 0.01683 0.00912 -0.0965 0.4417 1.0000
7.250 1.2149 0.01724 0.00953 -0.0945 0.4303 1.0000
7.500 1.2299 0.01771 0.00996 -0.0925 0.4191 1.0000
7.750 1.2435 0.01825 0.01045 -0.0904 0.4076 1.0000
8.000 1.2581 0.01878 0.01099 -0.0885 0.3955 1.0000
8.250 1.2719 0.01938 0.01156 -0.0865 0.3838 1.0000
8.500 1.2844 0.02005 0.01221 -0.0844 0.3721 1.0000
8.750 1.2971 0.02075 0.01290 -0.0824 0.3597 1.0000
9.000 1.3094 0.02151 0.01365 -0.0805 0.3472 1.0000
9.250 1.3204 0.02235 0.01447 -0.0784 0.3348 1.0000
9.500 1.3301 0.02330 0.01539 -0.0763 0.3222 1.0000
9.750 1.3395 0.02432 0.01639 -0.0743 0.3094 1.0000
10.000 1.3492 0.02536 0.01742 -0.0724 0.2969 1.0000
10.250 1.3578 0.02651 0.01855 -0.0705 0.2852 1.0000
10.500 1.3648 0.02780 0.01981 -0.0685 0.2743 1.0000
10.750 1.3734 0.02904 0.02105 -0.0668 0.2635 1.0000
11.000 1.3812 0.03036 0.02238 -0.0651 0.2540 1.0000
11.250 1.3875 0.03181 0.02382 -0.0633 0.2448 1.0000
11.500 1.3958 0.03318 0.02520 -0.0618 0.2365 1.0000
11.750 1.4015 0.03476 0.02678 -0.0602 0.2284 1.0000
12.000 1.4095 0.03622 0.02828 -0.0588 0.2208 1.0000
12.250 1.4149 0.03791 0.02997 -0.0574 0.2133 1.0000
12.500 1.4222 0.03950 0.03160 -0.0561 0.2067 1.0000
12.750 1.4290 0.04117 0.03330 -0.0549 0.2002 1.0000
13.000 1.4335 0.04305 0.03519 -0.0536 0.1948 1.0000
13.250 1.4427 0.04459 0.03681 -0.0527 0.1894 1.0000
13.500 1.4488 0.04641 0.03867 -0.0516 0.1842 1.0000
13.750 1.4532 0.04842 0.04068 -0.0506 0.1798 1.0000
14.000 1.4617 0.05010 0.04246 -0.0498 0.1749 1.0000
14.250 1.4671 0.05209 0.04449 -0.0490 0.1701 1.0000
14.500 1.4700 0.05435 0.04674 -0.0481 0.1657 1.0000
14.750 1.4772 0.05625 0.04874 -0.0475 0.1606 1.0000
15.000 1.4806 0.05855 0.05107 -0.0469 0.1555 1.0000
15.250 1.4828 0.06101 0.05354 -0.0463 0.1511 1.0000
15.500 1.4888 0.06312 0.05575 -0.0459 0.1466 1.0000
15.750 1.4918 0.06555 0.05823 -0.0454 0.1425 1.0000
16.000 1.4928 0.06821 0.06091 -0.0450 0.1391 1.0000
16.250 1.4983 0.07041 0.06321 -0.0447 0.1358 1.0000
16.500 1.5021 0.07285 0.06574 -0.0444 0.1322 1.0000
16.750 1.5036 0.07557 0.06852 -0.0443 0.1286 1.0000
17.250 1.5068 0.08107 0.07417 -0.0441 0.1218 1.0000
17.500 1.5082 0.08390 0.07710 -0.0442 0.1182 1.0000
17.750 1.5073 0.08703 0.08028 -0.0443 0.1149 1.0000
18.000 1.5064 0.09017 0.08347 -0.0445 0.1121 1.0000
18.250 1.5091 0.09295 0.08641 -0.0448 0.1088 1.0000
18.500 1.5090 0.09611 0.08968 -0.0452 0.1053 1.0000
18.750 1.5058 0.09971 0.09334 -0.0457 0.1019 1.0000
19.000 1.5053 0.10297 0.09672 -0.0463 0.0984 1.0000
19.250 1.5042 0.10636 0.10024 -0.0471 0.0938 1.0000
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