GOE 620 AIRFOIL (goe620-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: GOE 620 AIRFOIL (goe620-il) Reynolds number: 1,000,000 Max Cl/Cd: 117.55 at α=3.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-goe620-il-1000000.txt Download as CSV file: xf-goe620-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: GOE 620 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
------ -------- --------- --------- -------- -------- --------
-16.750 -0.6728 0.07496 0.07225 -0.1074 0.9947 0.0317
-16.500 -0.6913 0.06687 0.06401 -0.1152 0.9930 0.0320
-16.250 -0.7104 0.05985 0.05684 -0.1215 0.9902 0.0321
-16.000 -0.7184 0.05414 0.05099 -0.1275 0.9873 0.0323
-15.750 -0.7212 0.04894 0.04566 -0.1336 0.9844 0.0324
-15.500 -0.7181 0.04421 0.04082 -0.1398 0.9820 0.0325
-15.250 -0.7137 0.04008 0.03657 -0.1450 0.9783 0.0326
-15.000 -0.7162 0.03548 0.03183 -0.1500 0.9718 0.0329
-14.750 -0.7042 0.03176 0.02801 -0.1557 0.9678 0.0332
-14.500 -0.6899 0.02892 0.02509 -0.1601 0.9596 0.0335
-14.250 -0.6606 0.02662 0.02272 -0.1662 0.9544 0.0339
-14.000 -0.6280 0.02457 0.02059 -0.1725 0.9486 0.0342
-13.750 -0.5968 0.02300 0.01891 -0.1773 0.9400 0.0345
-13.500 -0.5704 0.02183 0.01763 -0.1800 0.9291 0.0348
-13.250 -0.5477 0.02102 0.01670 -0.1811 0.9165 0.0353
-13.000 -0.5358 0.02025 0.01580 -0.1799 0.9012 0.0356
-12.750 -0.5292 0.01967 0.01510 -0.1771 0.8854 0.0359
-12.500 -0.5235 0.01919 0.01450 -0.1739 0.8707 0.0361
-12.250 -0.5117 0.01871 0.01391 -0.1716 0.8582 0.0363
-12.000 -0.4978 0.01829 0.01336 -0.1697 0.8468 0.0366
-11.750 -0.4821 0.01792 0.01291 -0.1679 0.8367 0.0368
-11.500 -0.4679 0.01738 0.01226 -0.1659 0.8272 0.0371
-11.250 -0.4568 0.01656 0.01137 -0.1636 0.8179 0.0375
-11.000 -0.4401 0.01610 0.01084 -0.1619 0.8099 0.0379
-10.750 -0.4211 0.01570 0.01040 -0.1606 0.8031 0.0383
-10.500 -0.4010 0.01538 0.01003 -0.1594 0.7963 0.0387
-10.250 -0.3800 0.01509 0.00968 -0.1582 0.7901 0.0392
-10.000 -0.3585 0.01477 0.00931 -0.1572 0.7841 0.0396
-9.750 -0.3368 0.01450 0.00897 -0.1561 0.7778 0.0402
-9.500 -0.3144 0.01425 0.00864 -0.1552 0.7723 0.0407
-9.250 -0.2911 0.01397 0.00833 -0.1544 0.7678 0.0412
-9.000 -0.2675 0.01375 0.00804 -0.1536 0.7630 0.0415
-8.750 -0.2476 0.01325 0.00747 -0.1523 0.7585 0.0421
-8.500 -0.2261 0.01284 0.00703 -0.1512 0.7540 0.0427
-8.250 -0.2025 0.01255 0.00673 -0.1504 0.7506 0.0433
-8.000 -0.1783 0.01230 0.00646 -0.1497 0.7467 0.0440
-7.750 -0.1539 0.01208 0.00620 -0.1490 0.7428 0.0447
-7.500 -0.1293 0.01189 0.00595 -0.1484 0.7388 0.0454
-7.250 -0.1039 0.01171 0.00573 -0.1478 0.7350 0.0461
-7.000 -0.0780 0.01156 0.00555 -0.1473 0.7320 0.0467
-6.750 -0.0554 0.01115 0.00513 -0.1464 0.7286 0.0477
-6.500 -0.0310 0.01090 0.00486 -0.1457 0.7250 0.0487
-6.250 -0.0058 0.01072 0.00465 -0.1451 0.7212 0.0496
-6.000 0.0203 0.01059 0.00446 -0.1446 0.7171 0.0506
-5.750 0.0459 0.01042 0.00428 -0.1441 0.7144 0.0516
-5.500 0.0721 0.01028 0.00413 -0.1436 0.7112 0.0523
-5.250 0.0964 0.00999 0.00382 -0.1429 0.7077 0.0540
-5.000 0.1218 0.00983 0.00364 -0.1423 0.7039 0.0556
-4.750 0.1480 0.00973 0.00349 -0.1418 0.6998 0.0571
-4.500 0.1743 0.00961 0.00336 -0.1414 0.6966 0.0584
-4.250 0.1995 0.00939 0.00316 -0.1407 0.6933 0.0609
-4.000 0.2252 0.00924 0.00301 -0.1402 0.6894 0.0634
-3.750 0.2509 0.00912 0.00287 -0.1396 0.6854 0.0667
-3.500 0.2764 0.00900 0.00275 -0.1390 0.6810 0.0736
-3.250 0.3010 0.00876 0.00263 -0.1383 0.6775 0.0959
-3.000 0.3258 0.00854 0.00252 -0.1376 0.6734 0.1200
-2.750 0.3506 0.00838 0.00243 -0.1370 0.6689 0.1413
-2.500 0.3755 0.00828 0.00237 -0.1363 0.6643 0.1627
-2.250 0.4010 0.00820 0.00234 -0.1357 0.6598 0.1807
-2.000 0.4265 0.00811 0.00230 -0.1351 0.6549 0.1962
-1.750 0.4510 0.00805 0.00226 -0.1343 0.6487 0.2096
-1.500 0.4753 0.00803 0.00224 -0.1334 0.6424 0.2207
-1.250 0.5003 0.00797 0.00221 -0.1327 0.6356 0.2331
-1.000 0.5229 0.00795 0.00219 -0.1315 0.6274 0.2477
-0.750 0.5470 0.00791 0.00218 -0.1306 0.6194 0.2601
-0.500 0.5689 0.00793 0.00217 -0.1292 0.6098 0.2717
-0.250 0.5918 0.00791 0.00217 -0.1281 0.6004 0.2862
0.000 0.6118 0.00795 0.00219 -0.1264 0.5900 0.3003
0.250 0.6331 0.00795 0.00220 -0.1249 0.5795 0.3165
0.500 0.6511 0.00799 0.00223 -0.1228 0.5694 0.3310
0.750 0.6704 0.00802 0.00227 -0.1209 0.5596 0.3477
1.000 0.6896 0.00806 0.00232 -0.1191 0.5507 0.3672
1.250 0.7094 0.00811 0.00239 -0.1173 0.5417 0.3865
1.500 0.7283 0.00819 0.00248 -0.1155 0.5326 0.4057
1.750 0.7471 0.00828 0.00258 -0.1136 0.5231 0.4262
2.000 0.7663 0.00836 0.00269 -0.1118 0.5142 0.4523
2.250 0.7852 0.00843 0.00282 -0.1099 0.5058 0.4859
2.500 0.8038 0.00851 0.00296 -0.1081 0.4986 0.5206
2.750 0.8239 0.00856 0.00309 -0.1065 0.4918 0.5568
3.000 0.8408 0.00867 0.00325 -0.1043 0.4843 0.5927
3.250 0.8605 0.00869 0.00338 -0.1027 0.4779 0.6360
3.500 0.9898 0.00842 0.00384 -0.1250 0.4642 0.9840
3.750 1.0094 0.00862 0.00401 -0.1233 0.4573 1.0000
4.000 1.0261 0.00883 0.00416 -0.1211 0.4495 1.0000
4.250 1.0459 0.00900 0.00430 -0.1196 0.4429 1.0000
4.500 1.0646 0.00920 0.00446 -0.1178 0.4347 1.0000
4.750 1.0827 0.00943 0.00464 -0.1160 0.4275 1.0000
5.000 1.1025 0.00963 0.00482 -0.1145 0.4197 1.0000
5.250 1.1198 0.00991 0.00505 -0.1127 0.4115 1.0000
5.500 1.1399 0.01013 0.00524 -0.1113 0.4038 1.0000
6.000 1.1763 0.01071 0.00575 -0.1081 0.3860 1.0000
6.250 1.1921 0.01110 0.00607 -0.1061 0.3756 1.0000
6.500 1.2102 0.01144 0.00637 -0.1046 0.3654 1.0000
6.750 1.2273 0.01183 0.00672 -0.1029 0.3561 1.0000
7.000 1.2428 0.01228 0.00712 -0.1010 0.3449 1.0000
7.250 1.2599 0.01270 0.00750 -0.0995 0.3342 1.0000
7.500 1.2746 0.01323 0.00797 -0.0976 0.3238 1.0000
7.750 1.2909 0.01372 0.00843 -0.0960 0.3135 1.0000
8.000 1.3060 0.01428 0.00894 -0.0943 0.3035 1.0000
8.500 1.3357 0.01548 0.01006 -0.0910 0.2843 1.0000
9.000 1.3656 0.01674 0.01127 -0.0880 0.2689 1.0000
9.250 1.3787 0.01750 0.01199 -0.0863 0.2611 1.0000
9.500 1.3946 0.01813 0.01261 -0.0850 0.2549 1.0000
9.750 1.4081 0.01890 0.01336 -0.0835 0.2480 1.0000
10.000 1.4221 0.01967 0.01411 -0.0821 0.2422 1.0000
10.250 1.4381 0.02033 0.01479 -0.0810 0.2382 1.0000
10.500 1.4520 0.02114 0.01559 -0.0797 0.2326 1.0000
10.750 1.4640 0.02208 0.01652 -0.0782 0.2271 1.0000
11.000 1.4799 0.02280 0.01725 -0.0772 0.2228 1.0000
11.250 1.4927 0.02373 0.01818 -0.0759 0.2175 1.0000
11.500 1.5037 0.02479 0.01922 -0.0745 0.2113 1.0000
11.750 1.5157 0.02580 0.02023 -0.0732 0.2033 1.0000
12.000 1.5240 0.02709 0.02148 -0.0717 0.1925 1.0000
12.250 1.5298 0.02859 0.02292 -0.0700 0.1797 1.0000
12.500 1.5234 0.03099 0.02515 -0.0674 0.1521 1.0000
12.750 1.5174 0.03346 0.02750 -0.0651 0.1349 1.0000
13.000 1.5237 0.03506 0.02910 -0.0637 0.1300 1.0000
13.250 1.5310 0.03662 0.03068 -0.0625 0.1272 1.0000
13.500 1.5382 0.03820 0.03228 -0.0614 0.1249 1.0000
13.750 1.5429 0.04003 0.03412 -0.0602 0.1219 1.0000
14.000 1.5504 0.04165 0.03577 -0.0592 0.1203 1.0000
14.250 1.5556 0.04351 0.03767 -0.0582 0.1181 1.0000
14.500 1.5654 0.04496 0.03917 -0.0574 0.1171 1.0000
14.750 1.5739 0.04655 0.04081 -0.0567 0.1160 1.0000
15.000 1.5806 0.04835 0.04266 -0.0559 0.1147 1.0000
15.250 1.5873 0.05014 0.04449 -0.0551 0.1137 1.0000
15.500 1.5917 0.05221 0.04661 -0.0544 0.1124 1.0000
15.750 1.5957 0.05431 0.04876 -0.0536 0.1111 1.0000
16.000 1.5985 0.05658 0.05107 -0.0529 0.1099 1.0000
16.250 1.5989 0.05912 0.05366 -0.0522 0.1083 1.0000
16.500 1.5989 0.06175 0.05634 -0.0516 0.1068 1.0000
16.750 1.6072 0.06354 0.05820 -0.0513 0.1062 1.0000
17.000 1.6141 0.06547 0.06019 -0.0509 0.1055 1.0000
17.250 1.6201 0.06749 0.06228 -0.0506 0.1047 1.0000
17.500 1.6249 0.06967 0.06452 -0.0503 0.1037 1.0000
17.750 1.6292 0.07192 0.06683 -0.0501 0.1026 1.0000
18.000 1.6313 0.07444 0.06940 -0.0498 0.1012 1.0000
18.250 1.6318 0.07717 0.07218 -0.0497 0.1000 1.0000
18.500 1.6307 0.08008 0.07513 -0.0495 0.0986 1.0000
18.750 1.6262 0.08342 0.07853 -0.0494 0.0970 1.0000
19.000 1.6283 0.08598 0.08115 -0.0494 0.0957 1.0000
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Polar data table (+)
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