OAF128 AIRFOIL (oaf128-il) Xfoil prediction polar at RE=200,000 Ncrit=5
| Details | Polar file |
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Airfoil: OAF128 AIRFOIL (oaf128-il) Reynolds number: 200,000 Max Cl/Cd: 55.53 at α=6.5° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-oaf128-il-200000-n5.txt Download as CSV file: xf-oaf128-il-200000-n5.csv |
XFOIL Version 6.96
Calculated polar for: OAF128 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
------ -------- --------- --------- -------- -------- --------
-15.750 -1.0174 0.12102 0.11651 0.0313 1.0000 0.0253
-15.500 -1.0529 0.10880 0.10405 0.0236 1.0000 0.0253
-15.250 -1.0790 0.09920 0.09424 0.0175 1.0000 0.0253
-15.000 -1.1011 0.09103 0.08587 0.0124 1.0000 0.0254
-14.750 -1.1201 0.08375 0.07840 0.0079 1.0000 0.0255
-14.500 -1.1353 0.07731 0.07179 0.0039 1.0000 0.0256
-14.250 -1.1417 0.07262 0.06702 0.0014 1.0000 0.0257
-14.000 -1.1475 0.06800 0.06232 -0.0012 1.0000 0.0259
-13.750 -1.1526 0.06349 0.05771 -0.0038 1.0000 0.0261
-13.500 -1.1567 0.05910 0.05323 -0.0065 1.0000 0.0263
-13.250 -1.1596 0.05487 0.04889 -0.0092 1.0000 0.0266
-13.000 -1.1611 0.05087 0.04477 -0.0119 1.0000 0.0268
-12.750 -1.1613 0.04712 0.04089 -0.0144 1.0000 0.0271
-12.500 -1.1608 0.04369 0.03732 -0.0166 1.0000 0.0275
-12.250 -1.1610 0.04070 0.03418 -0.0180 1.0000 0.0278
-12.000 -1.1546 0.03834 0.03165 -0.0187 1.0000 0.0282
-11.750 -1.1435 0.03633 0.02948 -0.0190 1.0000 0.0286
-11.500 -1.1293 0.03453 0.02751 -0.0191 1.0000 0.0291
-11.250 -1.1133 0.03287 0.02575 -0.0192 1.0000 0.0296
-11.000 -1.0955 0.03136 0.02421 -0.0193 1.0000 0.0302
-10.750 -1.0758 0.03000 0.02278 -0.0195 1.0000 0.0308
-10.500 -1.0546 0.02874 0.02144 -0.0197 1.0000 0.0317
-10.250 -1.0322 0.02756 0.02016 -0.0198 1.0000 0.0327
-10.000 -1.0088 0.02644 0.01892 -0.0200 1.0000 0.0338
-9.750 -0.9853 0.02529 0.01774 -0.0204 1.0000 0.0348
-9.500 -0.9605 0.02428 0.01668 -0.0207 1.0000 0.0361
-9.250 -0.9349 0.02333 0.01564 -0.0210 1.0000 0.0375
-9.000 -0.9089 0.02237 0.01462 -0.0214 1.0000 0.0389
-8.750 -0.8823 0.02148 0.01370 -0.0218 1.0000 0.0407
-8.500 -0.8549 0.02071 0.01284 -0.0222 1.0000 0.0432
-8.250 -0.8275 0.01987 0.01200 -0.0227 1.0000 0.0459
-8.000 -0.7993 0.01915 0.01123 -0.0231 1.0000 0.0494
-7.750 -0.7710 0.01840 0.01048 -0.0236 1.0000 0.0538
-7.500 -0.7423 0.01771 0.00980 -0.0241 1.0000 0.0602
-7.250 -0.7133 0.01707 0.00920 -0.0246 1.0000 0.0696
-7.000 -0.6841 0.01648 0.00866 -0.0252 1.0000 0.0813
-6.750 -0.6547 0.01596 0.00819 -0.0257 1.0000 0.0942
-6.500 -0.6250 0.01550 0.00776 -0.0262 1.0000 0.1067
-6.250 -0.5952 0.01506 0.00735 -0.0267 1.0000 0.1186
-6.000 -0.5653 0.01464 0.00697 -0.0273 1.0000 0.1308
-5.750 -0.5352 0.01425 0.00663 -0.0278 1.0000 0.1436
-5.500 -0.5049 0.01389 0.00634 -0.0284 1.0000 0.1578
-5.250 -0.4745 0.01356 0.00608 -0.0290 1.0000 0.1736
-4.750 -0.4108 0.01313 0.00571 -0.0306 0.9309 0.2100
-4.500 -0.3836 0.01300 0.00559 -0.0301 0.8956 0.2252
-4.250 -0.3573 0.01288 0.00546 -0.0294 0.8659 0.2391
-4.000 -0.3307 0.01278 0.00532 -0.0288 0.8385 0.2539
-3.750 -0.3034 0.01268 0.00517 -0.0283 0.8124 0.2690
-3.500 -0.2757 0.01260 0.00503 -0.0279 0.7869 0.2844
-3.250 -0.2477 0.01253 0.00489 -0.0276 0.7622 0.3001
-3.000 -0.2192 0.01247 0.00476 -0.0274 0.7380 0.3155
-2.750 -0.1902 0.01242 0.00464 -0.0273 0.7151 0.3308
-2.500 -0.1610 0.01237 0.00454 -0.0273 0.6935 0.3457
-2.250 -0.1317 0.01234 0.00445 -0.0273 0.6731 0.3600
-2.000 -0.1022 0.01231 0.00436 -0.0273 0.6537 0.3741
-1.750 -0.0725 0.01230 0.00429 -0.0274 0.6358 0.3887
-1.500 -0.0428 0.01229 0.00424 -0.0276 0.6197 0.4051
-1.250 -0.0130 0.01228 0.00421 -0.0277 0.6036 0.4219
-1.000 0.0167 0.01227 0.00417 -0.0278 0.5870 0.4360
-0.750 0.0465 0.01228 0.00412 -0.0279 0.5694 0.4488
-0.250 0.1062 0.01229 0.00408 -0.0283 0.5368 0.4750
0.000 0.1361 0.01230 0.00408 -0.0284 0.5242 0.4878
0.250 0.1660 0.01233 0.00408 -0.0286 0.5118 0.5017
0.500 0.1959 0.01234 0.00411 -0.0288 0.4991 0.5175
0.750 0.2258 0.01234 0.00415 -0.0289 0.4877 0.5350
1.000 0.2555 0.01237 0.00419 -0.0291 0.4768 0.5539
1.250 0.2853 0.01237 0.00426 -0.0292 0.4649 0.5740
1.500 0.3150 0.01240 0.00433 -0.0294 0.4538 0.5957
1.750 0.3443 0.01240 0.00442 -0.0294 0.4427 0.6212
2.000 0.3735 0.01241 0.00453 -0.0294 0.4321 0.6519
2.250 0.4020 0.01243 0.00463 -0.0292 0.4211 0.6856
2.500 0.4303 0.01242 0.00476 -0.0290 0.4095 0.7216
2.750 0.4579 0.01244 0.00488 -0.0285 0.3988 0.7599
3.000 0.4844 0.01246 0.00497 -0.0278 0.3850 0.8012
3.250 0.5097 0.01246 0.00502 -0.0268 0.3677 0.8450
3.500 0.5335 0.01243 0.00502 -0.0255 0.3505 0.8965
3.750 0.5612 0.01233 0.00495 -0.0251 0.3348 1.0000
4.000 0.5915 0.01256 0.00510 -0.0255 0.3194 1.0000
4.250 0.6216 0.01279 0.00528 -0.0259 0.3042 1.0000
4.500 0.6516 0.01305 0.00547 -0.0263 0.2889 1.0000
4.750 0.6815 0.01333 0.00567 -0.0267 0.2733 1.0000
5.000 0.7111 0.01362 0.00591 -0.0270 0.2574 1.0000
5.250 0.7406 0.01395 0.00616 -0.0273 0.2416 1.0000
5.500 0.7699 0.01430 0.00644 -0.0277 0.2264 1.0000
5.750 0.7990 0.01468 0.00676 -0.0280 0.2113 1.0000
6.000 0.8279 0.01507 0.00710 -0.0283 0.1958 1.0000
6.250 0.8567 0.01548 0.00746 -0.0285 0.1788 1.0000
6.500 0.8851 0.01594 0.00785 -0.0288 0.1607 1.0000
6.750 0.9132 0.01646 0.00828 -0.0291 0.1439 1.0000
7.000 0.9411 0.01702 0.00877 -0.0293 0.1301 1.0000
7.250 0.9687 0.01759 0.00930 -0.0295 0.1195 1.0000
7.500 0.9960 0.01818 0.00986 -0.0297 0.1115 1.0000
7.750 1.0229 0.01881 0.01047 -0.0298 0.1046 1.0000
8.000 1.0498 0.01939 0.01108 -0.0298 0.0993 1.0000
8.250 1.0760 0.02005 0.01173 -0.0299 0.0945 1.0000
8.500 1.1019 0.02072 0.01242 -0.0299 0.0905 1.0000
8.750 1.1278 0.02135 0.01311 -0.0298 0.0866 1.0000
9.000 1.1525 0.02212 0.01386 -0.0297 0.0833 1.0000
9.250 1.1771 0.02285 0.01465 -0.0296 0.0804 1.0000
9.500 1.2016 0.02356 0.01543 -0.0294 0.0775 1.0000
9.750 1.2250 0.02436 0.01625 -0.0291 0.0749 1.0000
10.000 1.2470 0.02529 0.01720 -0.0288 0.0727 1.0000
10.250 1.2699 0.02607 0.01808 -0.0284 0.0703 1.0000
10.500 1.2916 0.02692 0.01901 -0.0280 0.0681 1.0000
10.750 1.3119 0.02787 0.02000 -0.0275 0.0662 1.0000
11.000 1.3304 0.02897 0.02112 -0.0269 0.0645 1.0000
11.250 1.3495 0.02994 0.02223 -0.0263 0.0627 1.0000
11.500 1.3670 0.03099 0.02338 -0.0256 0.0609 1.0000
11.750 1.3826 0.03213 0.02459 -0.0247 0.0594 1.0000
12.000 1.3950 0.03344 0.02594 -0.0237 0.0581 1.0000
12.250 1.4052 0.03486 0.02745 -0.0226 0.0569 1.0000
12.500 1.4115 0.03638 0.02912 -0.0212 0.0557 1.0000
12.750 1.4167 0.03822 0.03109 -0.0204 0.0545 1.0000
13.000 1.4217 0.04030 0.03328 -0.0201 0.0534 1.0000
13.250 1.4261 0.04263 0.03570 -0.0203 0.0524 1.0000
13.500 1.4294 0.04521 0.03835 -0.0207 0.0516 1.0000
13.750 1.4314 0.04804 0.04125 -0.0213 0.0508 1.0000
14.000 1.4330 0.05111 0.04451 -0.0222 0.0498 1.0000
14.250 1.4332 0.05439 0.04796 -0.0232 0.0488 1.0000
14.500 1.4322 0.05789 0.05158 -0.0244 0.0480 1.0000
14.750 1.4300 0.06158 0.05539 -0.0258 0.0472 1.0000
15.000 1.4269 0.06543 0.05934 -0.0273 0.0465 1.0000
15.250 1.4230 0.06941 0.06340 -0.0288 0.0459 1.0000
15.500 1.4185 0.07342 0.06747 -0.0303 0.0453 1.0000
15.750 1.4110 0.07803 0.07222 -0.0322 0.0447 1.0000
16.000 1.4004 0.08321 0.07760 -0.0344 0.0441 1.0000
16.250 1.3894 0.08864 0.08320 -0.0369 0.0434 1.0000
16.500 1.3781 0.09432 0.08904 -0.0397 0.0428 1.0000
16.750 1.3667 0.10016 0.09502 -0.0426 0.0422 1.0000
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