LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Xfoil prediction polar at RE=1,000,000 Ncrit=9
| Details | Polar file |
|---|---|
|
Airfoil: LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il) Reynolds number: 1,000,000 Max Cl/Cd: 89.72 at α=1.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-c141f-il-1000000.txt Download as CSV file: xf-c141f-il-1000000.csv |
XFOIL Version 6.96
Calculated polar for: LOCKHEED C-141 BL958.89 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
------ -------- --------- --------- -------- -------- --------
-10.750 -0.4577 0.11376 0.11192 -0.0269 1.0000 0.0220
-10.500 -0.4877 0.10479 0.10296 -0.0307 1.0000 0.0236
-9.750 -0.7417 0.02371 0.01968 -0.0750 0.9853 0.0235
-9.500 -0.7194 0.02113 0.01675 -0.0757 0.9845 0.0239
-9.250 -0.6986 0.02037 0.01593 -0.0748 0.9823 0.0242
-9.000 -0.6735 0.01989 0.01543 -0.0746 0.9803 0.0245
-8.750 -0.6451 0.01949 0.01498 -0.0750 0.9789 0.0248
-8.500 -0.6158 0.01905 0.01450 -0.0757 0.9777 0.0253
-8.250 -0.5863 0.01834 0.01369 -0.0764 0.9767 0.0257
-8.000 -0.5566 0.01739 0.01258 -0.0772 0.9758 0.0262
-7.750 -0.5257 0.01660 0.01163 -0.0782 0.9752 0.0267
-7.500 -0.4937 0.01595 0.01084 -0.0793 0.9746 0.0270
-7.250 -0.4627 0.01481 0.00962 -0.0805 0.9741 0.0276
-7.000 -0.4298 0.01440 0.00921 -0.0817 0.9736 0.0281
-6.750 -0.3970 0.01408 0.00886 -0.0829 0.9730 0.0286
-6.500 -0.3732 0.01377 0.00852 -0.0820 0.9701 0.0291
-6.250 -0.3467 0.01336 0.00806 -0.0817 0.9675 0.0297
-6.000 -0.3170 0.01293 0.00757 -0.0821 0.9657 0.0303
-5.750 -0.2861 0.01262 0.00719 -0.0827 0.9642 0.0306
-5.500 -0.2571 0.01181 0.00637 -0.0831 0.9628 0.0314
-5.250 -0.2266 0.01149 0.00607 -0.0836 0.9614 0.0320
-5.000 -0.1961 0.01120 0.00577 -0.0841 0.9601 0.0327
-4.750 -0.1698 0.01097 0.00552 -0.0837 0.9573 0.0335
-4.500 -0.1442 0.01075 0.00528 -0.0831 0.9537 0.0343
-4.250 -0.1171 0.01040 0.00490 -0.0828 0.9508 0.0349
-4.000 -0.0897 0.00994 0.00447 -0.0826 0.9484 0.0359
-3.750 -0.0610 0.00968 0.00421 -0.0826 0.9460 0.0368
-3.500 -0.0350 0.00945 0.00399 -0.0820 0.9419 0.0377
-3.250 -0.0091 0.00922 0.00375 -0.0813 0.9369 0.0387
-3.000 0.0179 0.00888 0.00340 -0.0810 0.9330 0.0399
-2.750 0.0455 0.00861 0.00315 -0.0807 0.9296 0.0412
-2.500 0.0718 0.00842 0.00297 -0.0802 0.9246 0.0426
-2.250 0.0989 0.00823 0.00278 -0.0798 0.9193 0.0438
-2.000 0.1262 0.00794 0.00249 -0.0795 0.9147 0.0456
-1.750 0.1534 0.00776 0.00233 -0.0791 0.9086 0.0476
-1.500 0.1804 0.00759 0.00217 -0.0787 0.9003 0.0495
-1.250 0.2078 0.00737 0.00196 -0.0783 0.8923 0.0522
-1.000 0.2353 0.00722 0.00181 -0.0780 0.8819 0.0550
-0.750 0.2625 0.00706 0.00165 -0.0776 0.8676 0.0590
-0.500 0.2898 0.00697 0.00151 -0.0772 0.8502 0.0645
-0.250 0.3166 0.00691 0.00143 -0.0768 0.8302 0.0744
0.000 0.3433 0.00687 0.00138 -0.0763 0.8097 0.0904
0.250 0.3698 0.00684 0.00135 -0.0758 0.7890 0.1116
0.500 0.3960 0.00677 0.00133 -0.0754 0.7676 0.1518
0.750 0.4144 0.00541 0.00133 -0.0741 0.7448 0.6560
1.000 0.4356 0.00509 0.00140 -0.0725 0.7158 0.8018
1.250 0.4558 0.00508 0.00150 -0.0704 0.6798 0.8868
1.500 0.4750 0.00532 0.00162 -0.0681 0.6258 0.9362
1.750 0.4981 0.00576 0.00178 -0.0668 0.5509 0.9666
2.000 0.5238 0.00648 0.00200 -0.0665 0.4359 0.9837
2.250 0.5604 0.00732 0.00230 -0.0688 0.3169 0.9939
2.500 0.6036 0.00781 0.00250 -0.0724 0.2580 0.9986
2.750 0.6330 0.00807 0.00262 -0.0729 0.2313 1.0000
3.000 0.6547 0.00825 0.00271 -0.0716 0.2156 1.0000
3.250 0.6769 0.00842 0.00281 -0.0703 0.2032 1.0000
3.500 0.6993 0.00860 0.00292 -0.0692 0.1909 1.0000
3.750 0.7221 0.00878 0.00303 -0.0681 0.1788 1.0000
4.000 0.7452 0.00896 0.00316 -0.0670 0.1657 1.0000
4.250 0.7677 0.00921 0.00329 -0.0659 0.1459 1.0000
4.500 0.7895 0.00957 0.00348 -0.0647 0.1168 1.0000
4.750 0.8121 0.00990 0.00370 -0.0636 0.1003 1.0000
5.000 0.8359 0.01017 0.00391 -0.0627 0.0927 1.0000
5.250 0.8597 0.01045 0.00414 -0.0619 0.0873 1.0000
5.500 0.8842 0.01068 0.00436 -0.0612 0.0837 1.0000
5.750 0.9090 0.01090 0.00456 -0.0606 0.0809 1.0000
6.000 0.9332 0.01117 0.00480 -0.0599 0.0776 1.0000
6.250 0.9574 0.01144 0.00507 -0.0592 0.0749 1.0000
6.500 0.9825 0.01164 0.00527 -0.0586 0.0731 1.0000
6.750 1.0072 0.01187 0.00550 -0.0580 0.0711 1.0000
7.000 1.0312 0.01216 0.00576 -0.0573 0.0689 1.0000
7.250 1.0547 0.01249 0.00609 -0.0565 0.0667 1.0000
7.500 1.0797 0.01267 0.00630 -0.0560 0.0653 1.0000
7.750 1.1043 0.01289 0.00652 -0.0554 0.0633 1.0000
8.000 1.1281 0.01318 0.00679 -0.0547 0.0609 1.0000
8.250 1.1516 0.01348 0.00709 -0.0539 0.0588 1.0000
8.500 1.1762 0.01367 0.00730 -0.0534 0.0567 1.0000
8.750 1.1999 0.01394 0.00755 -0.0527 0.0539 1.0000
9.000 1.2235 0.01420 0.00782 -0.0519 0.0511 1.0000
9.250 1.2467 0.01449 0.00808 -0.0512 0.0471 1.0000
9.500 1.2694 0.01480 0.00837 -0.0504 0.0419 1.0000
9.750 1.2908 0.01522 0.00874 -0.0493 0.0360 1.0000
10.000 1.3111 0.01573 0.00922 -0.0481 0.0316 1.0000
10.250 1.3304 0.01628 0.00975 -0.0467 0.0286 1.0000
10.500 1.3494 0.01677 0.01026 -0.0452 0.0266 1.0000
10.750 1.3666 0.01736 0.01087 -0.0435 0.0249 1.0000
11.000 1.3851 0.01784 0.01139 -0.0419 0.0238 1.0000
11.250 1.4022 0.01843 0.01199 -0.0402 0.0227 1.0000
11.500 1.4176 0.01914 0.01273 -0.0383 0.0217 1.0000
11.750 1.4352 0.01966 0.01331 -0.0367 0.0211 1.0000
12.000 1.4518 0.02024 0.01394 -0.0351 0.0204 1.0000
12.250 1.4675 0.02089 0.01463 -0.0333 0.0198 1.0000
12.500 1.4810 0.02169 0.01547 -0.0313 0.0193 1.0000
12.750 1.4923 0.02264 0.01648 -0.0290 0.0187 1.0000
13.000 1.5070 0.02332 0.01723 -0.0273 0.0184 1.0000
13.250 1.5208 0.02408 0.01805 -0.0255 0.0181 1.0000
13.500 1.5334 0.02491 0.01895 -0.0236 0.0177 1.0000
13.750 1.5455 0.02578 0.01989 -0.0217 0.0174 1.0000
14.000 1.5567 0.02673 0.02089 -0.0198 0.0171 1.0000
14.250 1.5663 0.02779 0.02202 -0.0178 0.0168 1.0000
14.500 1.5731 0.02907 0.02336 -0.0157 0.0165 1.0000
14.750 1.5753 0.03073 0.02510 -0.0132 0.0162 1.0000
15.000 1.5772 0.03246 0.02693 -0.0110 0.0160 1.0000
15.250 1.5842 0.03387 0.02843 -0.0094 0.0159 1.0000
15.500 1.5898 0.03544 0.03009 -0.0078 0.0157 1.0000
15.750 1.5939 0.03718 0.03193 -0.0063 0.0156 1.0000
16.000 1.5964 0.03915 0.03401 -0.0050 0.0154 1.0000
16.250 1.5976 0.04132 0.03627 -0.0038 0.0153 1.0000
16.500 1.5972 0.04374 0.03880 -0.0028 0.0152 1.0000
16.750 1.5953 0.04645 0.04162 -0.0021 0.0150 1.0000
17.000 1.5921 0.04947 0.04475 -0.0017 0.0149 1.0000
17.250 1.5869 0.05288 0.04828 -0.0017 0.0148 1.0000
17.500 1.5800 0.05673 0.05225 -0.0021 0.0147 1.0000
17.750 1.5708 0.06115 0.05679 -0.0031 0.0147 1.0000
18.000 1.5592 0.06615 0.06193 -0.0046 0.0146 1.0000
18.250 1.5441 0.07197 0.06789 -0.0067 0.0145 1.0000
18.500 1.5259 0.07865 0.07471 -0.0097 0.0145 1.0000
18.750 1.5034 0.08641 0.08264 -0.0134 0.0145 1.0000
19.000 1.4764 0.09522 0.09161 -0.0178 0.0145 1.0000
19.250 1.4472 0.10463 0.10118 -0.0226 0.0145 1.0000
|
Polar data table (+)
Polar graphs
<< Back to LOCKHEED C-141 BL958.89 AIRFOIL (c141f-il)