GOE 630 AIRFOIL (goe630-il) Xfoil prediction polar at RE=1,000,000 Ncrit=5
| Details | Polar file |
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Airfoil: GOE 630 AIRFOIL (goe630-il) Reynolds number: 1,000,000 Max Cl/Cd: 123.14 at α=5.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-goe630-il-1000000-n5.txt Download as CSV file: xf-goe630-il-1000000-n5.csv |
XFOIL Version 6.96
Calculated polar for: GOE 630 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 = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-11.500 0.0454 0.09770 0.09481 -0.1145 0.7735 0.0131
-11.250 0.0526 0.09532 0.09238 -0.1154 0.7632 0.0135
-11.000 0.0461 0.08996 0.08697 -0.1171 0.7535 0.0150
-10.500 0.0634 0.08603 0.08297 -0.1186 0.7369 0.0153
-10.250 0.0722 0.08414 0.08105 -0.1192 0.7289 0.0154
-10.000 0.0828 0.08251 0.07940 -0.1198 0.7232 0.0156
-9.750 0.0900 0.08029 0.07717 -0.1206 0.7164 0.0158
-9.500 0.0989 0.07847 0.07532 -0.1212 0.7113 0.0163
-9.250 0.1040 0.07591 0.07276 -0.1220 0.7064 0.0167
-9.000 0.0919 0.07053 0.06738 -0.1238 0.7017 0.0180
-8.750 0.0996 0.06883 0.06567 -0.1242 0.6957 0.0182
-7.250 0.0064 0.01663 0.01201 -0.1536 0.6717 0.0240
-7.000 0.0284 0.01534 0.01047 -0.1531 0.6663 0.0242
-6.750 0.0519 0.01450 0.00942 -0.1526 0.6607 0.0245
-6.500 0.0766 0.01379 0.00856 -0.1522 0.6555 0.0246
-6.250 0.1019 0.01326 0.00789 -0.1517 0.6495 0.0247
-6.000 0.1263 0.01267 0.00712 -0.1512 0.6429 0.0249
-5.750 0.1515 0.01207 0.00640 -0.1508 0.6367 0.0253
-5.500 0.1773 0.01174 0.00599 -0.1503 0.6296 0.0255
-5.250 0.2035 0.01146 0.00564 -0.1500 0.6234 0.0257
-5.000 0.2299 0.01123 0.00533 -0.1496 0.6156 0.0260
-4.750 0.2561 0.01104 0.00507 -0.1492 0.6078 0.0263
-4.500 0.2826 0.01088 0.00485 -0.1488 0.5992 0.0267
-4.250 0.3087 0.01069 0.00457 -0.1484 0.5913 0.0270
-4.000 0.3348 0.01049 0.00429 -0.1479 0.5817 0.0273
-3.750 0.3607 0.01031 0.00402 -0.1475 0.5722 0.0276
-3.500 0.3862 0.01018 0.00379 -0.1469 0.5609 0.0279
-3.250 0.4122 0.01003 0.00357 -0.1464 0.5506 0.0282
-3.000 0.4381 0.00993 0.00338 -0.1459 0.5412 0.0285
-2.750 0.4638 0.00985 0.00323 -0.1454 0.5306 0.0287
-2.500 0.4896 0.00977 0.00308 -0.1449 0.5200 0.0289
-2.250 0.5146 0.00965 0.00289 -0.1443 0.5086 0.0295
-2.000 0.5400 0.00961 0.00278 -0.1437 0.4977 0.0300
-1.750 0.5659 0.00958 0.00271 -0.1432 0.4884 0.0305
-1.500 0.5913 0.00959 0.00267 -0.1427 0.4792 0.0311
-1.250 0.6172 0.00958 0.00262 -0.1422 0.4705 0.0318
-1.000 0.6426 0.00960 0.00258 -0.1417 0.4620 0.0325
-0.750 0.6682 0.00960 0.00254 -0.1412 0.4534 0.0331
-0.500 0.6934 0.00963 0.00252 -0.1406 0.4451 0.0336
-0.250 0.7186 0.00963 0.00248 -0.1400 0.4364 0.0348
0.000 0.7436 0.00967 0.00249 -0.1394 0.4292 0.0358
0.250 0.7693 0.00969 0.00250 -0.1389 0.4229 0.0371
0.500 0.7942 0.00975 0.00252 -0.1383 0.4163 0.0383
0.750 0.8195 0.00978 0.00254 -0.1378 0.4109 0.0398
1.000 0.8446 0.00982 0.00257 -0.1372 0.4052 0.0420
1.250 0.8691 0.00990 0.00263 -0.1365 0.3993 0.0445
1.500 0.8941 0.00995 0.00267 -0.1360 0.3943 0.0471
1.750 0.9188 0.01001 0.00272 -0.1353 0.3885 0.0504
2.000 0.9425 0.01012 0.00279 -0.1346 0.3825 0.0528
2.250 0.9672 0.01016 0.00285 -0.1339 0.3784 0.0579
2.500 0.9915 0.01022 0.00292 -0.1333 0.3740 0.0652
2.750 1.0149 0.01027 0.00303 -0.1324 0.3694 0.0927
3.000 1.0377 0.01032 0.00315 -0.1315 0.3652 0.1370
3.250 1.0612 0.01033 0.00328 -0.1308 0.3618 0.1969
3.500 1.0838 0.01031 0.00342 -0.1298 0.3581 0.2730
3.750 1.1035 0.01016 0.00363 -0.1284 0.3540 0.4667
4.250 1.1940 0.00974 0.00418 -0.1369 0.3451 1.0000
4.500 1.2168 0.00989 0.00431 -0.1360 0.3415 1.0000
4.750 1.2387 0.01006 0.00446 -0.1349 0.3381 1.0000
5.000 1.2587 0.01025 0.00462 -0.1335 0.3346 1.0000
5.250 1.2792 0.01041 0.00477 -0.1321 0.3321 1.0000
5.500 1.3004 0.01056 0.00492 -0.1309 0.3298 1.0000
5.750 1.3212 0.01073 0.00509 -0.1297 0.3272 1.0000
6.000 1.3417 0.01091 0.00527 -0.1284 0.3245 1.0000
6.250 1.3619 0.01112 0.00547 -0.1271 0.3217 1.0000
6.500 1.3814 0.01136 0.00569 -0.1257 0.3188 1.0000
6.750 1.4020 0.01157 0.00591 -0.1246 0.3162 1.0000
7.000 1.4232 0.01177 0.00612 -0.1236 0.3142 1.0000
7.250 1.4440 0.01198 0.00636 -0.1225 0.3118 1.0000
7.500 1.4644 0.01222 0.00661 -0.1214 0.3095 1.0000
7.750 1.4842 0.01249 0.00689 -0.1203 0.3071 1.0000
8.000 1.5033 0.01280 0.00719 -0.1191 0.3045 1.0000
8.250 1.5218 0.01314 0.00754 -0.1178 0.3013 1.0000
8.500 1.5425 0.01340 0.00782 -0.1169 0.2978 1.0000
8.750 1.5605 0.01378 0.00819 -0.1156 0.2913 1.0000
9.000 1.5768 0.01425 0.00864 -0.1141 0.2861 1.0000
9.250 1.5963 0.01459 0.00901 -0.1131 0.2809 1.0000
9.500 1.6136 0.01504 0.00946 -0.1119 0.2760 1.0000
9.750 1.6294 0.01558 0.00999 -0.1105 0.2709 1.0000
10.000 1.6467 0.01606 0.01048 -0.1093 0.2639 1.0000
10.250 1.6613 0.01670 0.01111 -0.1079 0.2576 1.0000
10.500 1.6774 0.01727 0.01169 -0.1067 0.2516 1.0000
10.750 1.6916 0.01796 0.01238 -0.1053 0.2449 1.0000
11.000 1.7043 0.01877 0.01317 -0.1038 0.2355 1.0000
11.250 1.7127 0.01986 0.01421 -0.1019 0.2220 1.0000
11.500 1.7172 0.02124 0.01552 -0.0996 0.2047 1.0000
12.000 1.7031 0.02582 0.01981 -0.0935 0.1547 1.0000
12.250 1.6937 0.02846 0.02233 -0.0906 0.1321 1.0000
12.500 1.6730 0.03218 0.02588 -0.0872 0.1002 1.0000
12.750 1.6592 0.03554 0.02915 -0.0847 0.0803 1.0000
13.000 1.6523 0.03847 0.03206 -0.0829 0.0675 1.0000
13.250 1.6346 0.04252 0.03603 -0.0808 0.0471 1.0000
13.500 1.6125 0.04727 0.04073 -0.0789 0.0280 1.0000
13.750 1.6057 0.05064 0.04412 -0.0779 0.0216 1.0000
14.000 1.6039 0.05352 0.04705 -0.0771 0.0192 1.0000
14.250 1.6010 0.05661 0.05019 -0.0765 0.0171 1.0000
14.500 1.5998 0.05957 0.05321 -0.0759 0.0158 1.0000
14.750 1.5980 0.06264 0.05635 -0.0755 0.0150 1.0000
15.000 1.5946 0.06594 0.05972 -0.0751 0.0141 1.0000
15.250 1.5914 0.06928 0.06313 -0.0748 0.0135 1.0000
15.500 1.5885 0.07263 0.06657 -0.0746 0.0131 1.0000
15.750 1.5839 0.07625 0.07026 -0.0745 0.0124 1.0000
16.000 1.5786 0.07994 0.07403 -0.0745 0.0120 1.0000
16.250 1.5728 0.08378 0.07794 -0.0745 0.0117 1.0000
16.500 1.5652 0.08787 0.08210 -0.0746 0.0111 1.0000
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Polar data table (+)
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