OAF117 AIRFOIL (oaf117-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
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Airfoil: OAF117 AIRFOIL (oaf117-il) Reynolds number: 1,000,000 Max Cl/Cd: 96.84 at α=5.5° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-oaf117-il-1000000.txt Download as CSV file: xf-oaf117-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: OAF117 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
------ -------- --------- --------- -------- -------- --------
-16.000 -1.2517 0.07922 0.07628 0.0022 1.0000 0.0160
-15.750 -1.2887 0.06971 0.06663 -0.0036 1.0000 0.0160
-15.500 -1.3273 0.05997 0.05674 -0.0098 1.0000 0.0159
-15.250 -1.3639 0.05024 0.04684 -0.0166 1.0000 0.0158
-15.000 -1.3944 0.04068 0.03708 -0.0248 1.0000 0.0158
-14.750 -1.3931 0.03314 0.02929 -0.0362 1.0000 0.0160
-14.500 -1.3784 0.03089 0.02693 -0.0381 1.0000 0.0163
-14.250 -1.3604 0.02922 0.02516 -0.0392 1.0000 0.0166
-14.000 -1.3405 0.02782 0.02366 -0.0400 1.0000 0.0170
-13.750 -1.3190 0.02660 0.02234 -0.0406 1.0000 0.0174
-13.500 -1.2963 0.02555 0.02119 -0.0410 1.0000 0.0177
-13.250 -1.2727 0.02459 0.02013 -0.0414 1.0000 0.0180
-13.000 -1.2513 0.02294 0.01840 -0.0423 1.0000 0.0187
-12.750 -1.2263 0.02209 0.01750 -0.0426 1.0000 0.0193
-12.500 -1.2004 0.02140 0.01677 -0.0429 1.0000 0.0198
-12.250 -1.1742 0.02074 0.01604 -0.0432 1.0000 0.0204
-12.000 -1.1476 0.02010 0.01534 -0.0435 1.0000 0.0209
-11.750 -1.1205 0.01958 0.01473 -0.0437 1.0000 0.0213
-11.500 -1.0946 0.01841 0.01350 -0.0443 1.0000 0.0222
-11.250 -1.0672 0.01780 0.01286 -0.0447 1.0000 0.0229
-11.000 -1.0394 0.01729 0.01231 -0.0450 1.0000 0.0236
-10.750 -1.0113 0.01683 0.01181 -0.0452 1.0000 0.0244
-10.500 -0.9830 0.01647 0.01139 -0.0454 1.0000 0.0250
-10.250 -0.9550 0.01567 0.01054 -0.0459 1.0000 0.0261
-10.000 -0.9265 0.01517 0.01003 -0.0463 1.0000 0.0270
-9.750 -0.8977 0.01477 0.00960 -0.0466 1.0000 0.0279
-9.500 -0.8688 0.01443 0.00922 -0.0468 1.0000 0.0288
-9.250 -0.8397 0.01403 0.00878 -0.0471 1.0000 0.0297
-9.000 -0.8106 0.01343 0.00817 -0.0476 1.0000 0.0311
-8.750 -0.7813 0.01308 0.00780 -0.0479 1.0000 0.0323
-8.500 -0.7519 0.01277 0.00746 -0.0482 1.0000 0.0334
-8.250 -0.7224 0.01246 0.00712 -0.0485 1.0000 0.0345
-8.000 -0.6927 0.01196 0.00662 -0.0490 1.0000 0.0365
-7.750 -0.6630 0.01166 0.00631 -0.0493 1.0000 0.0380
-7.500 -0.6333 0.01140 0.00603 -0.0496 1.0000 0.0394
-7.250 -0.6033 0.01100 0.00562 -0.0500 1.0000 0.0416
-7.000 -0.5733 0.01070 0.00533 -0.0504 1.0000 0.0438
-6.750 -0.5433 0.01047 0.00509 -0.0507 1.0000 0.0456
-6.500 -0.5130 0.01012 0.00474 -0.0511 1.0000 0.0486
-6.250 -0.4828 0.00985 0.00450 -0.0515 1.0000 0.0517
-6.000 -0.4525 0.00959 0.00423 -0.0519 1.0000 0.0550
-5.750 -0.4237 0.00952 0.00413 -0.0518 0.9373 0.0595
-5.500 -0.3980 0.00943 0.00395 -0.0510 0.9036 0.0647
-5.250 -0.3703 0.00929 0.00375 -0.0507 0.8762 0.0720
-5.000 -0.3416 0.00910 0.00354 -0.0506 0.8510 0.0842
-4.750 -0.3126 0.00892 0.00336 -0.0507 0.8255 0.1011
-4.500 -0.2833 0.00879 0.00321 -0.0508 0.8009 0.1167
-4.250 -0.2537 0.00869 0.00306 -0.0510 0.7776 0.1290
-4.000 -0.2241 0.00860 0.00293 -0.0511 0.7565 0.1395
-3.750 -0.1943 0.00851 0.00280 -0.0513 0.7360 0.1516
-3.500 -0.1644 0.00842 0.00270 -0.0515 0.7157 0.1660
-3.250 -0.1345 0.00836 0.00260 -0.0517 0.6960 0.1805
-2.750 -0.0746 0.00822 0.00243 -0.0522 0.6594 0.2083
-2.500 -0.0446 0.00815 0.00236 -0.0525 0.6436 0.2249
-2.250 -0.0146 0.00809 0.00230 -0.0527 0.6285 0.2425
-2.000 0.0154 0.00803 0.00225 -0.0530 0.6138 0.2619
-1.750 0.0454 0.00796 0.00221 -0.0532 0.5999 0.2822
-1.500 0.0754 0.00791 0.00218 -0.0535 0.5862 0.3060
-1.250 0.1054 0.00789 0.00216 -0.0537 0.5725 0.3250
-1.000 0.1353 0.00788 0.00214 -0.0539 0.5595 0.3408
-0.750 0.1653 0.00786 0.00214 -0.0541 0.5471 0.3569
-0.500 0.1952 0.00785 0.00213 -0.0543 0.5348 0.3721
-0.250 0.2252 0.00786 0.00213 -0.0545 0.5223 0.3865
0.250 0.2849 0.00789 0.00215 -0.0549 0.4952 0.4175
0.500 0.3148 0.00791 0.00217 -0.0551 0.4815 0.4339
0.750 0.3447 0.00793 0.00220 -0.0553 0.4692 0.4519
1.000 0.3745 0.00796 0.00223 -0.0555 0.4569 0.4690
1.250 0.4044 0.00798 0.00227 -0.0557 0.4449 0.4874
1.500 0.4342 0.00800 0.00232 -0.0559 0.4337 0.5085
1.750 0.4640 0.00804 0.00238 -0.0561 0.4218 0.5306
2.000 0.4938 0.00807 0.00243 -0.0564 0.4100 0.5534
2.250 0.5236 0.00808 0.00250 -0.0566 0.3987 0.5828
2.500 0.5533 0.00810 0.00259 -0.0568 0.3869 0.6200
2.750 0.5830 0.00811 0.00268 -0.0570 0.3748 0.6624
3.000 0.6126 0.00808 0.00278 -0.0572 0.3627 0.7136
3.250 0.6416 0.00801 0.00290 -0.0573 0.3510 0.7897
3.500 0.6633 0.00767 0.00291 -0.0555 0.3393 0.9403
3.750 0.6923 0.00774 0.00293 -0.0555 0.3256 1.0000
4.000 0.7219 0.00791 0.00304 -0.0557 0.3105 1.0000
4.250 0.7514 0.00812 0.00316 -0.0559 0.2929 1.0000
4.500 0.7808 0.00833 0.00329 -0.0561 0.2768 1.0000
4.750 0.8102 0.00854 0.00344 -0.0563 0.2626 1.0000
5.000 0.8395 0.00874 0.00359 -0.0565 0.2486 1.0000
5.250 0.8687 0.00898 0.00376 -0.0567 0.2314 1.0000
5.500 0.8977 0.00927 0.00394 -0.0569 0.2118 1.0000
5.750 0.9267 0.00957 0.00415 -0.0571 0.1927 1.0000
6.000 0.9554 0.00989 0.00438 -0.0573 0.1756 1.0000
6.250 0.9842 0.01020 0.00462 -0.0574 0.1613 1.0000
6.500 1.0128 0.01052 0.00488 -0.0576 0.1472 1.0000
6.750 1.0413 0.01085 0.00514 -0.0577 0.1336 1.0000
7.000 1.0696 0.01120 0.00542 -0.0579 0.1203 1.0000
7.250 1.0977 0.01159 0.00573 -0.0580 0.1058 1.0000
7.500 1.1255 0.01204 0.00607 -0.0581 0.0908 1.0000
7.750 1.1531 0.01250 0.00645 -0.0581 0.0772 1.0000
8.000 1.1805 0.01296 0.00684 -0.0582 0.0661 1.0000
8.250 1.2078 0.01343 0.00726 -0.0582 0.0572 1.0000
8.500 1.2348 0.01391 0.00770 -0.0582 0.0504 1.0000
8.750 1.2618 0.01435 0.00812 -0.0582 0.0459 1.0000
9.000 1.2887 0.01479 0.00856 -0.0581 0.0423 1.0000
9.250 1.3152 0.01526 0.00902 -0.0580 0.0394 1.0000
9.500 1.3415 0.01575 0.00952 -0.0578 0.0368 1.0000
9.750 1.3678 0.01618 0.00996 -0.0577 0.0349 1.0000
10.000 1.3931 0.01679 0.01057 -0.0575 0.0326 1.0000
10.250 1.4188 0.01725 0.01107 -0.0573 0.0313 1.0000
10.500 1.4443 0.01771 0.01156 -0.0570 0.0301 1.0000
10.750 1.4689 0.01828 0.01215 -0.0567 0.0288 1.0000
11.000 1.4916 0.01910 0.01300 -0.0562 0.0273 1.0000
11.250 1.5162 0.01958 0.01353 -0.0559 0.0267 1.0000
11.500 1.5399 0.02013 0.01412 -0.0555 0.0259 1.0000
11.750 1.5629 0.02073 0.01476 -0.0550 0.0251 1.0000
12.000 1.5844 0.02147 0.01553 -0.0544 0.0242 1.0000
12.250 1.6021 0.02261 0.01672 -0.0534 0.0232 1.0000
12.500 1.6235 0.02322 0.01739 -0.0527 0.0228 1.0000
12.750 1.6434 0.02394 0.01817 -0.0519 0.0223 1.0000
13.000 1.6618 0.02474 0.01904 -0.0509 0.0218 1.0000
13.250 1.6786 0.02561 0.01996 -0.0498 0.0213 1.0000
13.500 1.6929 0.02657 0.02098 -0.0484 0.0209 1.0000
13.750 1.7030 0.02774 0.02221 -0.0466 0.0205 1.0000
14.000 1.7046 0.02926 0.02381 -0.0440 0.0201 1.0000
14.250 1.6986 0.03163 0.02629 -0.0418 0.0198 1.0000
14.500 1.6919 0.03482 0.02960 -0.0412 0.0195 1.0000
14.750 1.6963 0.03721 0.03210 -0.0413 0.0194 1.0000
15.000 1.6991 0.04000 0.03500 -0.0418 0.0192 1.0000
15.250 1.6994 0.04322 0.03833 -0.0425 0.0190 1.0000
15.500 1.6976 0.04684 0.04206 -0.0435 0.0188 1.0000
15.750 1.6935 0.05082 0.04615 -0.0447 0.0186 1.0000
16.000 1.6867 0.05522 0.05066 -0.0461 0.0184 1.0000
16.250 1.6779 0.05992 0.05548 -0.0476 0.0183 1.0000
16.500 1.6659 0.06511 0.06078 -0.0493 0.0181 1.0000
16.750 1.6520 0.07061 0.06640 -0.0511 0.0180 1.0000
17.000 1.6362 0.07639 0.07229 -0.0531 0.0179 1.0000
17.250 1.6196 0.08248 0.07849 -0.0553 0.0178 1.0000
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Polar data table (+)
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