DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il) Xfoil prediction polar at RE=200,000 Ncrit=9
| Details | Polar file |
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Airfoil: DELFT DU84-132V3 AIRFOIL (MEASURED) (du84132v-il) Reynolds number: 200,000 Max Cl/Cd: 71.65 at α=6.25° Description: Mach=0 Ncrit=9 Source: Xfoil prediction Download polar: xf-du84132v-il-200000.txt Download as CSV file: xf-du84132v-il-200000.csv |
XFOIL Version 6.96
Calculated polar for: DELFT DU84-132V3 AIRFOIL (MEASURED)
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.200 e 6 Ncrit = 9.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-10.250 -0.3730 0.09993 0.09667 -0.0451 1.0000 0.0762
-10.000 -0.3758 0.09606 0.09285 -0.0433 1.0000 0.0769
-9.750 -0.4864 0.08990 0.08647 -0.0547 1.0000 0.0762
-9.500 -0.4601 0.08887 0.08550 -0.0487 1.0000 0.0772
-9.250 -0.4521 0.08822 0.08487 -0.0448 1.0000 0.0779
-9.000 -0.4543 0.08676 0.08345 -0.0422 1.0000 0.0786
-8.750 -0.4626 0.08487 0.08161 -0.0402 1.0000 0.0793
-8.500 -0.4774 0.08255 0.07936 -0.0387 1.0000 0.0801
-8.250 -0.4745 0.07671 0.07351 -0.0463 0.9951 0.0823
-8.000 -0.5264 0.06131 0.05737 -0.0693 0.9752 0.0892
-7.750 -0.4976 0.05820 0.05444 -0.0704 0.9723 0.0907
-7.500 -0.4684 0.05572 0.05196 -0.0729 0.9690 0.0928
-7.250 -0.4518 0.05259 0.04867 -0.0753 0.9618 0.0973
-7.000 -0.4186 0.02307 0.01731 -0.0814 0.9430 0.0577
-6.750 -0.4247 0.03288 0.02668 -0.0811 0.9482 0.0535
-6.250 -0.3617 0.02785 0.02063 -0.0833 0.9398 0.0472
-6.000 -0.3245 0.02597 0.01853 -0.0855 0.9377 0.0469
-5.750 -0.3012 0.02475 0.01715 -0.0848 0.9306 0.0467
-5.500 -0.2672 0.02349 0.01574 -0.0861 0.9267 0.0469
-5.250 -0.2295 0.02237 0.01449 -0.0879 0.9241 0.0472
-5.000 -0.1893 0.02144 0.01345 -0.0902 0.9222 0.0479
-4.750 -0.1681 0.02030 0.01240 -0.0892 0.9145 0.0495
-4.500 -0.1335 0.01940 0.01157 -0.0906 0.9107 0.0516
-4.250 -0.0943 0.01853 0.01071 -0.0929 0.9083 0.0541
-4.000 -0.0529 0.01759 0.00977 -0.0956 0.9066 0.0570
-3.750 -0.0291 0.01690 0.00913 -0.0951 0.8987 0.0616
-3.500 0.0086 0.01600 0.00828 -0.0971 0.8944 0.0769
-3.250 0.0465 0.01421 0.00740 -0.1001 0.8913 0.2559
-3.000 0.0774 0.01323 0.00706 -0.1012 0.8850 0.4121
-2.750 0.1071 0.01256 0.00682 -0.1015 0.8780 0.5191
-2.500 0.1395 0.01234 0.00716 -0.1011 0.8739 0.6423
-2.250 0.1646 0.01256 0.00738 -0.0998 0.8649 0.6883
-2.000 0.1989 0.01277 0.00753 -0.1000 0.8592 0.7213
-1.750 0.2262 0.01310 0.00780 -0.0989 0.8510 0.7420
-1.500 0.2559 0.01330 0.00794 -0.0982 0.8436 0.7576
-1.250 0.2809 0.01348 0.00807 -0.0968 0.8344 0.7712
-1.000 0.3106 0.01354 0.00804 -0.0964 0.8264 0.7844
-0.750 0.3324 0.01361 0.00807 -0.0945 0.8155 0.7957
-0.500 0.3581 0.01355 0.00796 -0.0932 0.8067 0.8058
-0.250 0.3830 0.01348 0.00783 -0.0921 0.7968 0.8162
0.000 0.4056 0.01347 0.00778 -0.0906 0.7865 0.8280
0.250 0.4272 0.01334 0.00762 -0.0884 0.7780 0.8408
0.500 0.4466 0.01318 0.00744 -0.0859 0.7677 0.8537
0.750 0.4676 0.01303 0.00723 -0.0838 0.7574 0.8654
1.000 0.4921 0.01294 0.00707 -0.0828 0.7469 0.8752
1.250 0.5142 0.01281 0.00690 -0.0812 0.7359 0.8822
1.500 0.5402 0.01276 0.00678 -0.0808 0.7246 0.8879
1.750 0.5639 0.01266 0.00666 -0.0798 0.7142 0.8926
2.000 0.5888 0.01261 0.00657 -0.0791 0.7042 0.8975
2.250 0.6157 0.01261 0.00652 -0.0790 0.6939 0.9015
2.500 0.6409 0.01258 0.00645 -0.0785 0.6817 0.9056
2.750 0.6634 0.01246 0.00630 -0.0772 0.6698 0.9107
3.000 0.6861 0.01243 0.00624 -0.0760 0.6573 0.9171
3.250 0.7081 0.01239 0.00618 -0.0748 0.6435 0.9225
3.500 0.7303 0.01233 0.00611 -0.0736 0.6297 0.9277
3.750 0.7542 0.01234 0.00607 -0.0728 0.6156 0.9325
4.000 0.7778 0.01238 0.00608 -0.0720 0.5998 0.9364
4.250 0.8008 0.01240 0.00605 -0.0710 0.5822 0.9401
4.500 0.8249 0.01249 0.00605 -0.0704 0.5640 0.9436
4.750 0.8479 0.01262 0.00613 -0.0696 0.5444 0.9471
5.000 0.8714 0.01276 0.00625 -0.0689 0.5256 0.9502
5.250 0.8958 0.01293 0.00639 -0.0685 0.5074 0.9539
5.500 0.9207 0.01314 0.00657 -0.0682 0.4886 0.9580
5.750 0.9455 0.01335 0.00679 -0.0679 0.4674 0.9623
6.000 0.9712 0.01359 0.00699 -0.0679 0.4449 0.9675
6.250 0.9981 0.01393 0.00726 -0.0682 0.4243 0.9750
6.500 1.0224 0.01430 0.00754 -0.0681 0.4038 1.0000
6.750 1.0429 0.01477 0.00789 -0.0672 0.3876 1.0000
7.000 1.0648 0.01524 0.00830 -0.0666 0.3726 1.0000
7.250 1.0875 0.01566 0.00874 -0.0662 0.3596 1.0000
7.500 1.1095 0.01608 0.00916 -0.0656 0.3475 1.0000
7.750 1.1301 0.01652 0.00959 -0.0647 0.3352 1.0000
8.000 1.1505 0.01692 0.01002 -0.0638 0.3225 1.0000
8.250 1.1699 0.01738 0.01050 -0.0628 0.3099 1.0000
8.500 1.1878 0.01789 0.01101 -0.0616 0.2964 1.0000
8.750 1.2047 0.01843 0.01155 -0.0602 0.2815 1.0000
9.000 1.2195 0.01903 0.01214 -0.0586 0.2641 1.0000
9.250 1.2325 0.01974 0.01282 -0.0567 0.2461 1.0000
9.500 1.2455 0.02046 0.01354 -0.0550 0.2225 1.0000
9.750 1.2541 0.02142 0.01436 -0.0527 0.1951 1.0000
10.000 1.2617 0.02255 0.01537 -0.0505 0.1700 1.0000
10.250 1.2671 0.02387 0.01655 -0.0483 0.1533 1.0000
10.500 1.2732 0.02524 0.01786 -0.0462 0.1431 1.0000
10.750 1.2795 0.02665 0.01925 -0.0442 0.1355 1.0000
11.000 1.2891 0.02790 0.02055 -0.0426 0.1280 1.0000
11.250 1.2979 0.02924 0.02192 -0.0411 0.1217 1.0000
11.500 1.3089 0.03043 0.02319 -0.0399 0.1146 1.0000
11.750 1.3171 0.03185 0.02464 -0.0386 0.1086 1.0000
12.000 1.3246 0.03335 0.02617 -0.0373 0.1027 1.0000
12.250 1.3284 0.03522 0.02802 -0.0358 0.0973 1.0000
12.500 1.3346 0.03697 0.02986 -0.0346 0.0919 1.0000
12.750 1.3356 0.03926 0.03208 -0.0333 0.0867 1.0000
13.000 1.3419 0.04113 0.03410 -0.0323 0.0822 1.0000
13.250 1.3464 0.04317 0.03622 -0.0314 0.0777 1.0000
13.500 1.3498 0.04558 0.03853 -0.0304 0.0731 1.0000
13.750 1.3542 0.04768 0.04087 -0.0298 0.0696 1.0000
14.000 1.3584 0.04991 0.04318 -0.0293 0.0660 1.0000
14.250 1.3617 0.05232 0.04557 -0.0288 0.0630 1.0000
14.500 1.3662 0.05474 0.04811 -0.0284 0.0601 1.0000
14.750 1.3697 0.05721 0.05073 -0.0282 0.0574 1.0000
15.000 1.3729 0.05975 0.05335 -0.0282 0.0552 1.0000
15.250 1.3759 0.06238 0.05598 -0.0283 0.0533 1.0000
15.500 1.3792 0.06513 0.05884 -0.0283 0.0514 1.0000
15.750 1.3801 0.06817 0.06205 -0.0286 0.0496 1.0000
16.000 1.3807 0.07129 0.06526 -0.0293 0.0478 1.0000
16.250 1.3805 0.07453 0.06854 -0.0302 0.0462 1.0000
16.500 1.3822 0.07761 0.07162 -0.0307 0.0444 1.0000
16.750 1.3795 0.08146 0.07567 -0.0318 0.0430 1.0000
17.000 1.3779 0.08521 0.07956 -0.0329 0.0417 1.0000
17.250 1.3778 0.08874 0.08317 -0.0340 0.0404 1.0000
17.500 1.3803 0.09183 0.08624 -0.0348 0.0390 1.0000
17.750 1.3807 0.09538 0.08989 -0.0355 0.0377 1.0000
18.000 1.3730 0.10035 0.09509 -0.0377 0.0368 1.0000
18.250 1.3667 0.10519 0.10012 -0.0397 0.0359 1.0000
18.500 1.3607 0.11003 0.10512 -0.0420 0.0349 1.0000
18.750 1.3591 0.11407 0.10922 -0.0439 0.0338 1.0000
19.000 1.3687 0.11588 0.11092 -0.0439 0.0321 1.0000
19.250 1.3521 0.12285 0.11817 -0.0480 0.0316 1.0000
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Polar data table (+)
Polar graphs
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