NREL's S807 Airfoil (s807-nr) Xfoil prediction polar at RE=500,000 Ncrit=5
| Details | Polar file |
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Airfoil: NREL's S807 Airfoil (s807-nr) Reynolds number: 500,000 Max Cl/Cd: 83.85 at α=9.25° Description: Mach=0 Ncrit=5 Source: Xfoil prediction Download polar: xf-s807-nr-500000-n5.txt Download as CSV file: xf-s807-nr-500000-n5.csv |
XFOIL Version 6.96
Calculated polar for: NREL's S807 Airfoil
1 1 Reynolds number fixed Mach number fixed
xtrf = 1.000 (top) 1.000 (bottom)
Mach = 0.000 Re = 0.500 e 6 Ncrit = 5.000
alpha CL CD CDp CM Top_Xtr Bot_Xtr
------ -------- --------- --------- -------- -------- --------
-19.750 -0.9582 0.11799 0.11361 -0.0348 1.0000 0.0119
-19.500 -0.9612 0.11421 0.10975 -0.0362 1.0000 0.0120
-19.250 -0.9644 0.11045 0.10591 -0.0375 1.0000 0.0121
-19.000 -0.9664 0.10692 0.10230 -0.0386 1.0000 0.0123
-18.750 -0.9683 0.10347 0.09878 -0.0396 1.0000 0.0124
-18.500 -0.9693 0.10020 0.09542 -0.0405 1.0000 0.0125
-18.250 -0.9701 0.09699 0.09213 -0.0413 1.0000 0.0127
-18.000 -0.9704 0.09395 0.08902 -0.0420 1.0000 0.0128
-17.750 -0.9701 0.09097 0.08595 -0.0426 1.0000 0.0129
-17.500 -0.9692 0.08816 0.08308 -0.0431 1.0000 0.0130
-17.250 -0.9706 0.08516 0.08004 -0.0436 1.0000 0.0132
-17.000 -0.9702 0.08241 0.07725 -0.0440 1.0000 0.0134
-16.750 -0.9697 0.07966 0.07446 -0.0443 1.0000 0.0136
-16.500 -0.9684 0.07709 0.07184 -0.0445 1.0000 0.0136
-16.250 -0.9659 0.07464 0.06936 -0.0448 1.0000 0.0140
-16.000 -0.9638 0.07222 0.06690 -0.0449 1.0000 0.0142
-15.750 -0.9608 0.06996 0.06459 -0.0449 1.0000 0.0144
-15.500 -0.9579 0.06769 0.06227 -0.0448 1.0000 0.0146
-15.250 -0.9549 0.06550 0.06003 -0.0447 1.0000 0.0148
-15.000 -0.9512 0.06343 0.05791 -0.0445 1.0000 0.0150
-14.750 -0.9481 0.06131 0.05574 -0.0443 1.0000 0.0152
-14.500 -0.9444 0.05932 0.05370 -0.0439 1.0000 0.0154
-14.250 -0.9402 0.05740 0.05173 -0.0435 1.0000 0.0156
-14.000 -0.9363 0.05548 0.04977 -0.0431 1.0000 0.0158
-13.750 -0.9311 0.05375 0.04798 -0.0425 1.0000 0.0160
-13.500 -0.9297 0.05168 0.04589 -0.0420 1.0000 0.0162
-13.250 -0.9289 0.04961 0.04380 -0.0413 1.0000 0.0165
-13.000 -0.9263 0.04777 0.04193 -0.0406 1.0000 0.0168
-12.750 -0.9230 0.04603 0.04016 -0.0398 1.0000 0.0172
-12.500 -0.9199 0.04434 0.03844 -0.0389 1.0000 0.0174
-12.250 -0.9171 0.04268 0.03675 -0.0379 1.0000 0.0177
-12.000 -0.9140 0.04113 0.03517 -0.0368 1.0000 0.0181
-11.750 -0.9122 0.03959 0.03360 -0.0355 1.0000 0.0185
-11.500 -0.9111 0.03804 0.03201 -0.0341 1.0000 0.0188
-11.250 -0.9098 0.03659 0.03052 -0.0325 1.0000 0.0191
-11.000 -0.9095 0.03510 0.02899 -0.0309 1.0000 0.0193
-10.750 -0.9114 0.03357 0.02744 -0.0289 1.0000 0.0196
-10.500 -0.9159 0.03197 0.02581 -0.0267 1.0000 0.0200
-10.250 -0.9208 0.03045 0.02426 -0.0242 1.0000 0.0202
-10.000 -0.9141 0.02886 0.02265 -0.0241 0.9987 0.0209
-9.750 -0.8998 0.02738 0.02114 -0.0251 0.9961 0.0215
-9.500 -0.8838 0.02594 0.01966 -0.0266 0.9934 0.0224
-9.250 -0.8660 0.02440 0.01808 -0.0283 0.9889 0.0236
-9.000 -0.8289 0.02269 0.01636 -0.0337 0.9841 0.0259
-8.750 -0.7886 0.02102 0.01467 -0.0394 0.9786 0.0294
-8.500 -0.7497 0.01925 0.01291 -0.0450 0.9724 0.0361
-8.250 -0.7052 0.01772 0.01140 -0.0513 0.9692 0.0482
-8.000 -0.6835 0.01659 0.01031 -0.0520 0.9616 0.0602
-7.750 -0.6517 0.01552 0.00932 -0.0546 0.9580 0.0786
-7.250 -0.5986 0.01342 0.00751 -0.0574 0.9492 0.1403
-7.000 -0.5694 0.01220 0.00652 -0.0594 0.9443 0.1914
-6.500 -0.5147 0.00970 0.00472 -0.0625 0.9310 0.3475
-6.250 -0.4871 0.00939 0.00452 -0.0626 0.9223 0.3811
-6.000 -0.4595 0.00920 0.00433 -0.0625 0.9106 0.3962
-5.750 -0.4260 0.00899 0.00409 -0.0635 0.8925 0.4069
-5.500 -0.3281 0.00878 0.00371 -0.0774 0.8432 0.4339
-5.250 -0.2914 0.00916 0.00367 -0.0789 0.7487 0.4420
-5.000 -0.2687 0.00945 0.00360 -0.0778 0.6798 0.4452
-4.750 -0.2449 0.00967 0.00351 -0.0769 0.6236 0.4473
-4.500 -0.2199 0.00981 0.00343 -0.0763 0.5765 0.4488
-4.250 -0.1938 0.00993 0.00337 -0.0759 0.5382 0.4505
-4.000 -0.1668 0.01002 0.00332 -0.0758 0.5083 0.4522
-3.750 -0.1393 0.01010 0.00327 -0.0757 0.4842 0.4537
-3.500 -0.1115 0.01016 0.00321 -0.0757 0.4640 0.4552
-3.000 -0.0550 0.01028 0.00311 -0.0758 0.4313 0.4587
-2.750 -0.0265 0.01033 0.00306 -0.0759 0.4177 0.4605
-2.500 0.0020 0.01038 0.00301 -0.0760 0.4054 0.4620
-2.250 0.0304 0.01044 0.00297 -0.0761 0.3940 0.4634
-2.000 0.0592 0.01046 0.00294 -0.0762 0.3849 0.4648
-1.750 0.0875 0.01050 0.00293 -0.0763 0.3766 0.4662
-1.500 0.1163 0.01052 0.00293 -0.0764 0.3695 0.4677
-1.250 0.1449 0.01057 0.00293 -0.0765 0.3624 0.4692
-1.000 0.1736 0.01062 0.00295 -0.0766 0.3566 0.4710
-0.750 0.2024 0.01067 0.00296 -0.0767 0.3507 0.4729
-0.500 0.2309 0.01074 0.00298 -0.0768 0.3446 0.4747
-0.250 0.2596 0.01080 0.00299 -0.0769 0.3394 0.4763
0.000 0.2884 0.01085 0.00301 -0.0771 0.3343 0.4779
0.250 0.3170 0.01092 0.00303 -0.0772 0.3295 0.4794
0.500 0.3453 0.01100 0.00307 -0.0772 0.3253 0.4809
0.750 0.3741 0.01103 0.00312 -0.0774 0.3219 0.4825
1.000 0.4028 0.01108 0.00318 -0.0774 0.3181 0.4841
1.250 0.4312 0.01115 0.00325 -0.0775 0.3144 0.4858
1.500 0.4595 0.01125 0.00333 -0.0775 0.3109 0.4878
1.750 0.4878 0.01134 0.00341 -0.0776 0.3076 0.4898
2.000 0.5165 0.01141 0.00348 -0.0777 0.3046 0.4919
2.250 0.5450 0.01149 0.00356 -0.0777 0.3012 0.4937
2.500 0.5733 0.01159 0.00364 -0.0778 0.2981 0.4955
2.750 0.6013 0.01170 0.00373 -0.0778 0.2952 0.4971
3.000 0.6292 0.01181 0.00385 -0.0777 0.2925 0.4988
3.250 0.6575 0.01189 0.00397 -0.0778 0.2904 0.5007
3.500 0.6858 0.01198 0.00410 -0.0778 0.2882 0.5025
3.750 0.7140 0.01208 0.00423 -0.0778 0.2858 0.5045
4.000 0.7419 0.01219 0.00436 -0.0778 0.2832 0.5067
4.250 0.7697 0.01232 0.00450 -0.0778 0.2806 0.5090
4.500 0.7972 0.01247 0.00464 -0.0777 0.2780 0.5113
4.750 0.8245 0.01265 0.00480 -0.0775 0.2757 0.5133
5.000 0.8525 0.01274 0.00496 -0.0775 0.2741 0.5153
5.250 0.8804 0.01285 0.00513 -0.0775 0.2721 0.5173
5.500 0.9080 0.01297 0.00531 -0.0774 0.2697 0.5195
5.750 0.9355 0.01310 0.00549 -0.0773 0.2672 0.5217
6.000 0.9626 0.01326 0.00567 -0.0772 0.2647 0.5240
6.250 0.9892 0.01344 0.00585 -0.0769 0.2614 0.5264
6.500 1.0163 0.01359 0.00604 -0.0768 0.2581 0.5287
6.750 1.0436 0.01371 0.00622 -0.0766 0.2549 0.5311
7.000 1.0705 0.01385 0.00641 -0.0765 0.2516 0.5337
7.250 1.0969 0.01401 0.00662 -0.0762 0.2480 0.5364
7.500 1.1226 0.01423 0.00684 -0.0758 0.2440 0.5390
7.750 1.1496 0.01435 0.00705 -0.0757 0.2404 0.5417
8.000 1.1760 0.01451 0.00726 -0.0754 0.2362 0.5445
8.250 1.2014 0.01471 0.00748 -0.0750 0.2315 0.5470
8.500 1.2269 0.01491 0.00772 -0.0746 0.2269 0.5495
8.750 1.2528 0.01507 0.00795 -0.0743 0.2206 0.5524
9.000 1.2770 0.01533 0.00822 -0.0737 0.2136 0.5556
9.250 1.3022 0.01553 0.00849 -0.0733 0.2064 0.5591
9.500 1.3257 0.01583 0.00879 -0.0726 0.1979 0.5626
10.000 1.3708 0.01654 0.00951 -0.0710 0.1744 0.5689
10.250 1.3901 0.01710 0.01001 -0.0698 0.1580 0.5722
10.500 1.4076 0.01775 0.01061 -0.0683 0.1421 0.5758
10.750 1.4229 0.01842 0.01124 -0.0664 0.1283 0.5794
11.250 1.4501 0.01987 0.01266 -0.0623 0.1055 0.5868
11.500 1.4637 0.02058 0.01340 -0.0602 0.0963 0.5913
11.750 1.4761 0.02135 0.01418 -0.0581 0.0884 0.5960
12.250 1.4972 0.02307 0.01595 -0.0536 0.0737 0.6046
12.500 1.5058 0.02404 0.01695 -0.0513 0.0674 0.6095
12.750 1.5122 0.02515 0.01808 -0.0488 0.0616 0.6144
13.000 1.5192 0.02624 0.01923 -0.0466 0.0566 0.6193
13.250 1.5224 0.02760 0.02064 -0.0442 0.0521 0.6249
13.500 1.5274 0.02891 0.02203 -0.0422 0.0486 0.6312
13.750 1.5281 0.03060 0.02378 -0.0401 0.0453 0.6373
14.000 1.5296 0.03235 0.02563 -0.0385 0.0430 0.6443
14.250 1.5293 0.03441 0.02780 -0.0371 0.0410 0.6513
14.500 1.5254 0.03700 0.03050 -0.0362 0.0392 0.6584
14.750 1.5190 0.04014 0.03377 -0.0359 0.0377 0.6658
15.000 1.5134 0.04359 0.03736 -0.0363 0.0365 0.6732
15.250 1.5045 0.04779 0.04172 -0.0373 0.0353 0.6813
15.500 1.4917 0.05286 0.04695 -0.0391 0.0343 0.6888
15.750 1.4757 0.05863 0.05288 -0.0413 0.0336 0.6967
16.000 1.4567 0.06498 0.05939 -0.0438 0.0329 0.7041
16.250 1.4366 0.07157 0.06614 -0.0465 0.0324 0.7120
16.500 1.4167 0.07816 0.07288 -0.0493 0.0319 0.7202
16.750 1.4002 0.08439 0.07926 -0.0520 0.0313 0.7299
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